Interfaces for vehicular retrieval, transportation, and/or deposition of payloads and methods thereof

ABSTRACT

Some embodiments of the disclosure are directed to latching interfaces of a vehicle. In some embodiments, the vehicle comprises a latch system including a plurality of latches configured to selectively interlock with a corresponding first plurality of latch receptacles of a respective payload. In some embodiments, the vehicle comprises a second plurality of latch receptacles disposed on exterior portions of the chassis of the vehicle. In some embodiments, the second plurality of latch receptacles correspond to the first plurality of latch receptacles. In some embodiments, a spatial arrangement of the second plurality of latch receptacles on the exterior portions of the chassis of the vehicle corresponds to a spatial arrangement of the first plurality of latch receptacles on exterior portions of the respective payload. In some embodiments, the second plurality of latch receptacles of the vehicle are configured to interlock with a latching interface of an external system.

FIELD OF THE DISCLOSURE

This disclosure relates generally to vehicles, such as on-road vehiclesand off-road vehicles including rover systems for retrieval,transportation, and/or deposition of payloads, and more particularly, toproviding vehicle and rover systems with improved terrainmaneuverability and/or adaptability for the retrieval, transportation,and/or deposition of payloads.

BACKGROUND OF THE DISCLOSURE

Currently, there is a vacuum in the lunar economy. On the surface of theMoon, for example, there exist few solutions for transporting modularpayloads, which may store supplies, tools, scientific samples, food,etc., from one location on the Moon's surface (e.g., a landing zone, alunar lander, etc.) to another location on the Moon's surface (e.g., alunar base or outpost, a stationary lunar rover vehicle, lunar lander,etc.). In addition to the transportation of modular payloads, fewsystems exist for the transportation and/or relocation of large payloadson the surface of the Moon, such as the relocation of lunar landers,which traditionally are incapable of being operated (e.g., driven) forrelocation/transportation. Moreover, there is a need for thesetransportation solutions to be modularly configured for the ease andefficiency of initial deposition on the surface of the Moon (or otherplanetary body).

SUMMARY

This summary is provided to introduce a selection of concepts in asimplified form that are further described below in the DetailedDisclosure. This summary is not intended to identify key features of theclaimed subject matter, nor is it intended to be used as an aid indetermining the scope of the claimed subject matter.

Some embodiments of the disclosure are directed to a rover. In someembodiments, the rover comprises a chassis, a plurality of control legscoupled to the chassis, and a plurality of propulsion components coupledto the plurality of control legs. In some embodiments, the rover furthercomprises one or more processors. In some embodiments, the plurality ofcontrol legs each includes a suspension system in communication with theone or more processors, wherein the suspension system is controllable bythe one or more processors to cause the plurality of control legs toselectively raise and/or lower the chassis with respect to a reference(e.g., a surface on which the rover is placed, gravity, etc.). In someembodiments, the plurality of propulsion components each includes amotor assembly in communication with the one or more processors, whereinthe motor assembly is controllable by the one or more processors todrive the plurality of propulsion components and selectively cause amotion of the rover. In some embodiments, the rover further comprises alatching system provided within interior portions of the chassis,wherein the latching system is configured to interlock with a payload.

Some embodiments of the disclosure are directed to the retrieval,transportation, and/or deposition of payloads. In some embodiments, therover is configured to identify and approach, via the plurality ofpropulsion components, a respective payload. In some embodiments, therover is configured to adjust a height of the chassis, via the pluralityof control legs, with respect to the reference to position the interiorportions of the chassis around a surface of the respective payload. Insome embodiments, the rover is configured to engage with, via thelatching system, at least a portion of the respective payload. In someembodiments, the rover is configured to adjust the height of thechassis, via the plurality of control legs, with respect to thereference to maintain the respective payload at one or more respectiveorientations with respect to the reference. In some embodiments, therover is configured to transport the respective payload, via theplurality of propulsion components, to a respective target location. Insome embodiments, at the respective target location, the rover isconfigured to adjust the height of the chassis, via the plurality ofcontrol legs, with respect to a reference and disengage from the portionof the respective payload, via the latching system, to deposit therespective payload at the respective target location.

Some embodiments of the disclosure are directed to multi-rovercollaboration. In some embodiments, a first rover is in communicationwith a second rover. In some embodiments, one or more processors of thefirst rover are configured to communicate with one or more processors ofthe second rover to perform a joint action. In some embodiments, the oneor more processors of the first rover are configured to selectivelycontrol components of the suspension system, the motor assembly, and/orthe latch system of the first rover to perform a first part of the jointaction. In some embodiments, the one or more processors of the secondrover are configured to selectively control components of the suspensionsystem, the motor assembly, and/or the latch system of the second roverto perform a second part of the joint action.

Some embodiments of the disclosure are directed to latching interfacesof a rover. In some embodiments, the rover comprises a latch systemincluding a plurality of latches configured to selectively interlockwith a corresponding first plurality of latch receptacles of arespective payload for the retrieval, transportation, and/or depositionof the respective payload by the rover. In some embodiments, the rovercomprises a second plurality of latch receptacles disposed on exteriorportions of the chassis of the rover. In some embodiments, the secondplurality of latch receptacles correspond to the first plurality oflatch receptacles. In some embodiments, a spatial arrangement of thesecond plurality of latch receptacles on the exterior portions of thechassis of the rover corresponds to a spatial arrangement of the firstplurality of latch receptacles on exterior portions of the respectivepayload. In some embodiments, the second plurality of latch receptaclesof the rover are configured to interlock with a latching interface of anexternal system for the retrieval, transportation, and/or deposition ofthe rover by the external system.

BRIEF DESCRIPTION OF THE DRAWINGS

The novel features believed to be characteristic of the disclosure areset forth in the appended claims. In the descriptions that follow, likeparts are marked throughout the specification and drawings with the samenumerals, respectively. The drawings are not necessarily drawn to scaleand certain may be shown in exaggerated or generalized form in theinterest of clarity and conciseness. The disclosure itself, however, aswell as a preferred mode of use, further objectives and advantagesthereof, will be best understood by reference to the following detaileddescription of illustrative embodiments when read in conjunction withthe accompanying drawings.

FIGS. 1A-1B are schematic views of exemplary systems for implementingrovers according to some embodiments of the disclosure.

FIGS. 2A-2B illustrate a perspective view and a partially sectionalperspective view, respectively, of an example rover according to someembodiments of the disclosure.

FIGS. 3A-3C illustrate examples of a suspension system and a motorassembly of a rover according to some embodiments of the disclosure.

FIG. 4 illustrates examples of modular payloads configured to beretrieved, transported, and/or deposited by a rover according to someembodiments of the disclosure.

FIGS. 5A-5H illustrate an example of retrieval of a modular payloadusing a rover according to some embodiments of the disclosure.

FIGS. 6A-6B illustrate an example of adaptive suspension of a roverduring transport of a modular payload according to some embodiments ofthe disclosure.

FIGS. 7A-7E illustrate examples of functional modules configured tointerface with a rover according to some embodiments of the disclosure.

FIGS. 8A-8D illustrate an example retrieval and transportation of alarge payload using a multi-rover system according to some embodimentsof the disclosure.

FIG. 9 illustrates another example retrieval of a large payload using amulti-rover system according to some embodiments of the disclosure.

FIG. 10 illustrates an example contingency operation using a roveraccording to some embodiments of the disclosure.

FIGS. 11A-11E illustrate examples of functional modules configured tointerface with a rover according to some embodiments of the disclosure.

FIG. 12 illustrates an example of a chassis locking interface of a roveraccording to some embodiments of the disclosure.

FIGS. 13A-13C illustrate an example of depositing a rover and arespective modular payload onto a surface using an external systemaccording to some embodiments of the disclosure.

DETAILED DESCRIPTION

In the following description, reference is made to the accompanyingdrawings which form a part hereof, and in which it is shown by way ofillustration specific examples that may be practiced. It is to beunderstood that other examples may be used and structural changes may bemade without departing from the scope of the examples of the disclosure.

Generally described, the present systems and methods thereof provide oneor more vehicles or rovers for the retrieval, transportation, and/ordeposition of payloads. A rover (e.g., a lunar rover) operating on thesurface of the Moon or other planetary body may be configured to (e.g.,autonomously) locate a respective payload, retrieve (e.g., lift) therespective payload, and transport the respective payload to a respectivedestination on the surface of the Moon. The rover may be provided with aplurality of subsystems including intercommunicated and/or intercoupledcomponents that enable the rover to perform such actions. The rover maybe further configured to adapt to unevenness in terrain (e.g.,unevenness in the surface of the Moon) during transportation of therespective payload. In instances where retrieval, transportation, and/ordeposition of large payloads are required, the rover may be configuredto function in tandem with one or more additional rovers of the same orsimilar build to coordinate large-scale retrievals, transportation,and/or deposition of the large payloads. The rover may be configured foradaptive utility, ranging from operation of a functional module todoubling as a rover vehicle. The rover may be configured for ease oftransition between multiple modes of transport (e.g., initial depositionon the surface of the Moon and subsequent retrieval from the surface ofthe Moon). Such rovers and associated processes will be described below.

As used herein, the term “rover” refers to a robotic device or a roboticvehicle configured to move across and/or explore a (e.g., planetary)surface. The rover may be a partially or fully autonomous roboticvehicle. As a robotic vehicle, the rover may be configured to transportmembers of a human spaceflight crew. The rover may be comprised ofhardware-based systems including electrical components in communicationwith one or more (e.g., internal and/or external) central processingunits. Although various embodiments are described herein with referenceto a rover, it should be understood that the features and/ordescriptions of such embodiments are optionally applicable to an on-roadand/or off-road vehicle, more generally.

FIGS. 1A-1B are schematic views of exemplary systems for implementingrovers according to some embodiments of the disclosure. The componentsof the systems 100 and/or 150, as well as the components of othersystems, hardware architectures, and software architectures discussedherein, may be combined, omitted, or organized into differentarchitectures for various examples.

Generally, in FIG. 1A, the system 100 may include a vehicle/rover 102with an electronic control unit (ECU) 104 that executes one or moreapplications, operating systems, rover systems and subsystem executableinstructions, among others. In some embodiments, the ECU 104 may includeone or more respective microprocessors, one or more application-specificintegrated circuit(s) (ASIC), or other similar devices. The ECU 104 mayalso include respective internal processing memory, an interfacecircuit, and bus lines for transferring data, sending commands, andcommunicating with the plurality of components of the rover 102. The ECU104 may also include a respective communication device (not shown) forsending data internally to components of the rover 102. In someembodiments, the ECU may be configured to communicate withcommunications unit 116 for communicating with externally hostedcomputing systems (e.g., external to the rover 102).

In an exemplary embodiment, the ECU 104 may additionally communicatewith a storage unit 114 (e.g., memory, such as a computer-readablestorage medium that stores instructions for the various functions orapplications implemented by the system 100) to execute one or moreapplications, operating systems, rover systems and subsystem executableinstructions, and the like that are stored on the storage unit 114. Inone or more embodiments, the storage unit 114 may be accessed by therover systems and subsystems to store data, for example, one or moreimages, graph-based representations, or otherwise, of a surroundingenvironment of the rover 102, one or more sets of locational coordinates(e.g., GPS/DGPS coordinates), and/or rover dynamic data associated withdynamic rover parameters of the rover 102.

In some embodiments, the ECU 104 may be configured to communicate withthe rover latch/retrieval system 106 of the rover 102 to operate therover 102 to (e.g., autonomously) control one or more retrievalfunctions of the rover 102. The one or more retrieval functions of therover may include, but are not limited to, engaging with a respectivepayload to lift the respective payload for subsequent transportation ofthe respective payload, and disengaging with the respective payload todeposit the respective payload. In some embodiments, the ECU 104 may beconfigured to communicate with power system 108 of the rover 102 tosupply power to the rover 102. In some embodiments, the power system 108includes battery modules electrically coupled to power distribution andcharging circuitry for supplying power to the systems of the rover 102,such as the ECU 104, the communications unit 116, and the like.

In some embodiments, the ECU 104 may be configured to communicate withthe rover suspension system 110 to operate the rover 102 to control oneor more suspension functions of the rover 102. The one or moresuspension functions may include, but are not limited to, raising and/orlowering the rover 102 with respect to a reference (e.g., a surface onwhich the rover 202 is configured to be placed or operate (e.g., thesurface of a moon)), and adapting to one or more portions of unevennessduring transportation of a respective payload. In some embodiments, theECU 104 may be configured to communicate with the rover motor assembly122 to operate the rover 102 to control one or more driving functions ofthe rover 102. The one or more driving functions may include, but arenot limited to, steering, braking, accelerating, turning, and the like.

In some embodiments, the ECU 104 may be configured to selectivelycommunicate with one or more subsystems of a rover functional module 118that may be selectively interfaced with the rover 102. For example, whena respective functional module 118 is interfaced with the rover 102, theECU 104 may communicate with one or more subsystems of the respectivefunctional module 118 to electrically and communicatively interface therover to the respective functional module 118 to enable one or morespecialized functions. The one or more specialized functions may includemanual operation of the rover 102 (e.g., as a rover vehicle), andoperation of the rover 102 as a scientific rover (e.g., for thecollection of data samples).

In some embodiments, the ECU 104 may additionally be configured tooperably control one or more sensor modules 120 of the rover 102. Theone or more sensor modules 120 may include one or more sensors (notshown), such as cameras, proximity sensors, ultraviolet light sensors,audio sensors, and the like, that are positioned at one or morepositions on or in the rover 102 to capture information (e.g., images,light intensities, sound waves, etc.) of at least the externalsurrounding environment of the rover 102 (e.g., a predetermined arealocated around (such as front/side/behind/below) the rover 102).

In particular, the one or more sensors that are positioned in or on therover 102 may be configured to capture data about (e.g., images of)payloads, rovers, surface integrity (e.g., integrity of the lunarterrain), users (e.g., astronauts), or more generally any agents orstructures in an environment of the rover 102 to be analyzed by the ECU104. In some embodiments, the one or more sensors may be configured tocapture data of the above and transmit respectiveimage/sound/light/motion/etc. data to the ECU 104. The ECU 104 may beconfigured to process the transmitted data to recognize locations,actions, existences, etc. of one or more agents/structures in anenvironment of the rover 102. The ECU 104 may be configured to, usingthe processed data, selectively (e.g., and autonomously) control thevarious systems described above (e.g., latch system 106, suspensionsystem 110, motor assembly 122, etc.) to operate the rover 102 toperform various actions, including retrieving, transporting, anddepositing modular payloads, as will be described later.

In some embodiments, as illustrated in FIG. 1B, system 150 can bedivided between multiple rover systems. For example, a first roversystem 160 optionally includes a rover 102 a, storage unit 114 a,communications unit 116 a, latch system 106 a, power system 108 a,suspension system 110 a, a functional module 118 a, sensor modules 120a, and motor assembly 122 a, optionally communicating over ECU 104 a. Asecond rover system 170 optionally includes a rover 102 b, storage unit114 b, communications unit 116 b, latch system 106 b, power system 108b, suspension system 110 b, a functional module 118 b, sensor modules120 b, and motor assembly 122 b, optionally communicating over ECU 104b. The details of the components for rover systems 150 and 170 aresimilar to the corresponding components discussed above with respect tosystem 100 and are not repeated here for brevity. The first rover system160 and the second rover system 170 optionally communicate via a wiredor wireless connection (e.g., via communications unit 116 a-116 b)between the two systems. It should be understood that, in embodiments inwhich the system 150 includes additional rovers (e.g., one, two, three,four, etc. additional rovers), the additional rovers may be configuredto communicate in a similar manner (e.g., communicatively interfaced viathe communications unit of each respective rover).

FIGS. 2A-2B illustrate a perspective view and a partially sectionalperspective view, respectively, of an example rover 202 according tosome embodiments of the disclosure. As discussed herein later, the rover202 may be characterized by adaptive utility enabled by the varioussubsystems of the rover 202, which are optionally, extensively containedwithin a central body cavity of the rover 202. As shown in FIG. 2A, therover 202 may comprise a chassis 203 forming the central body of therover 202. In some embodiments, the chassis 203 may comprise a firstside (e.g., left side in the view of FIG. 2A) 205, a second side (e.g.,right side in the view of FIG. 2B) 209, and a medial member 207 joiningtop portions of the first side 205 and the second side 209. For example,from a top view, the chassis 203 may have an “H” shape formed by thefirst side 205, the second side 209, and the medial member 207. As shownin FIG. 2A, in some embodiments, the chassis 203 of the rover 202includes an interior 201 (e.g., formed by the interior surfaces of thefirst side 205, the second side 209, and the medial member 207)configured to at least partially surround a respective modular payload,as discussed in more detail later.

In some embodiments, the rover 202 may comprise a plurality of controllegs 213 coupled to the chassis 203. For example, as shown in FIG. 2A, afirst pair of control legs are coupled to the first side 205 of thechassis 203, and a second pair of control legs 213 are coupled to thesecond side 209 of the chassis 203. As discussed in more detail withreference to FIGS. 3A-3C, the plurality of control legs each optionallycomprise the same or similar exemplary components. For example, asdiscussed in detail later, the plurality of control legs 213 may eachcomprise a suspension system (e.g., corresponding to suspension system110 in FIGS. 1A-1B) configured to be controlled (e.g., by ECU 104 inFIGS. 1A-1B) to selectively raise and/or lower the plurality of controllegs 213, to thus raise and/or lower the chassis 203 with respect to thereference (e.g., the lunar surface).

In some embodiments, the rover 202 may comprise a plurality ofpropulsion components (e.g., wheels) 215 coupled to the plurality ofcontrol legs 213. For example, as shown in FIG. 2A, a first pair ofpropulsion components are coupled to the first pair of control legs onthe first side 205 of the chassis 203, and a second pair of propulsioncomponents are coupled to the second pair of control legs on the secondside 209 of the chassis 203. In some embodiments, the plurality ofpropulsion components 215 are each configured to be driven by a motorassembly (e.g., corresponding to motor assembly 122 in FIGS. 1A-1B)associated with a given control leg 213 coupled to the propulsioncomponent 215. In some embodiments, as discussed in more detail later,the plurality of propulsion components 215 may each be selectivelydriven by a corresponding motor assembly to cause movement of the rover202 in a respective direction. While the plurality of propulsioncomponents 215 are illustrated in FIG. 2A as being wheels, it should beunderstood that, in some embodiments, alternative types of propulsioncomponents may be provided, such as tracks, sleds, travois, spheres, andthe like.

In some embodiments, the rover 202 may further comprise one or moresensors 220 (e.g., corresponding to the sensor modules 120 in FIGS.1A-1B). As shown in FIG. 2A, the one or more sensors 220 may be disposedat one or more external front and/or rear portions of the rover 202 tocapture the external surrounding environment of the rover 202. Forexample, the one or more sensors 220 may be disposed at external frontand/or rear portions of the rover 202, including, but not limited tofrontal and/or rear portions of the first side 205 of the chassis 203,and/or frontal and/or rear portions of the second side 209 of thechassis 203. In some embodiments, the one or more sensors 220 mayinclude RGB cameras that may capture RGB bands that are configured tocapture rich information about object appearance, as well asrelationships and interactions between the rover 202 and objects (e.g.,modular payloads, craters, rocks, other rovers, etc.) within thesurrounding environment of the rover 202. As discussed previously withrespect to FIGS. 1A-1B, the sensory information captured by the one ormore sensors 220 may be converted into data by the ECU 104 for use inthe operations of the rover 202.

In some embodiments, the rover 202 may include one or more deployableexterior components for use by various systems of the rover 202. Forexample, as shown in FIG. 2A, the rover 202 may comprise a deployablesolar panel array 211 for use by the rover power system (e.g.,corresponding to power system 108 in FIGS. 1A-1B) in charging one ormore battery modules of the rover 202. As another example, the rover 202may comprise a deployable high-gain antenna 212 for use by the rovercommunications unit (e.g., corresponding to communications unit 116 inFIGS. 1A-1B) in communications with externally hosted computing systemsand/or command centers.

As mentioned above, the chassis may house a plurality of variouscomponents that form the systems and subsystems of the rover 202. Inhighly concentrated environments (e.g., like a moon), dust, dirt, soil,and other substance mitigation can be vital for the effective andlong-lasting performance of the rover 202. Accordingly, as discussedbelow, the major systems of the rover 202, such as the suspensionsystem, the motor assembly, the latching system, and the ECU may bedisposed within portions of the chassis 203.

FIG. 2B illustrates example systems contained within a side (e.g., thesecond side 209) and a portion of the medial member 207 of the chassis203. It should be understood that the components illustrated in FIG. 2Band described herein with respect to the second side 209 also optionallyapply to those components of the first side 205. As shown in FIG. 2B, agiven side of the chassis 203, such as the second side 209, may includeinternal compartments/portions for housing the various components of therover 202. For example, for a respective control leg, a portion of therespective control leg is integral to the side of the chassis 203 towhich the respective control leg is coupled (e.g., is contained within acavity formed by the side of the chassis 203 to which the respectivecontrol leg is coupled). For the control leg 213 a coupled to side 209of chassis 203, a portion of the control leg 213 a includes a firstlower compartment 221B of the second side 209 of the chassis 203. Insome embodiments, the suspension system 210 of a respective control leg(e.g., control leg 213 a) may be disposed within a lower compartment(e.g., lower compartment 221B) of the cavity of the side of the chassis203 to which the respective control leg is coupled (e.g., the secondside 209), as shown. The suspension system 210 will be described in moredetail with reference to FIGS. 3A-3C, below.

In some embodiments, as shown in FIG. 2B, the rover latching system 206may be disposed within the cavity of the medial member 207 of thechassis 203. In some embodiments, components of the latching system 206may additionally or alternatively be disposed within upper compartmentsof a given side of the chassis 203. For example, as shown in FIG. 2B,some components of the latching system 206 are disposed within a firstupper compartment of the cavity of the second side 209 of the chassis203. The latching system 206 will be described in more detail withreference to FIGS. 5A-5H, below.

As mentioned above, each propulsion component of the plurality ofpropulsion components 215 of the rover 202 may be configured to bedriven by a motor assembly 222 associated with a given control legcoupled to the propulsion component. As discussed in more detail below,the motor assembly 222 optionally includes a steering actuator and awheel actuator each configured to produce a respectivepropulsion-producing movement of the propulsion component.

FIGS. 3A-3C illustrate examples of a suspension system 310 and a motorassembly 322 of a rover according to some embodiments of the disclosure.In some examples, suspension system 310 optionally corresponds tosuspension system 210, and motor assembly 322 optionally corresponds tomotor assembly 222, shown in FIG. 2B. As described above with referenceto FIGS. 2A-2B, the suspension system 310 of a given control leg 313 maybe disposed within a portion of the chassis 203, such as within lowercompartment 321B, as shown in FIG. 3A. As discussed below, thesuspension system 310 and the motor assembly 322 may be controllable toselectively operate movement, maneuverability, and adaptabilityfunctions of the rover. It should be understood that the belowdescriptions of the various suspension system and motor assemblycomponents of the control leg 313 shown in FIGS. 3A-3C optionally applyfor each control leg of the plurality of control legs (e.g., theplurality of control legs 213).

As shown in FIG. 3A, the suspension system 310 of the control leg 313may comprise a first coupling 329 and a second coupling 330 disposedwithin the lower compartment 321B of the control leg 313. In someembodiments, the control leg 313 may comprise an upper four-bar link 325coupled to the first coupling 329. Additionally, in some embodiments,the control leg 313 may comprise a lower four-bar link 327 coupled tothe second coupling 330, as shown in FIG. 3A. In some embodiments, thefirst coupling 329 optionally couples the upper four-bar link 325 to thesuspension system 310, which, as discussed in more detail below, isconfigured to cause a movement of the upper four-bar link 325 or respondto (e.g., absorb or deflect) a movement by the upper four-bar link 325.For example, the upper four-bar link 325 may be configured to be raisedor lowered (e.g., with respect to the surface on which the rover isplaced) in response to upward or downward movements of the propulsioncomponent 315 or in response to operations of the suspension system 310,as discussed herein later. In some embodiments, the second coupling 329optionally provides provision for rotational movement of the lowerfour-bar link 327. For example, the lower four-bar link 327 may beconfigured to rotate bidirectionally (e.g., clockwise orcounterclockwise) in response to upward or downward movements of thepropulsion component 315 or in response to upward or downward movementsof the upper four-bar link 327. For example, in some instances, anupward (e.g., with respect to the surface on which the rover is placed)motion of the propulsion component optionally causes the upper four-barlink 325 and the lower four-bar link 327 to move upwardly in accordancewith the upward motion of the propulsion component 315. Similarly, adownward motion of the propulsion component optionally causes the upperfour-bar link 325 and the lower four-bar link 327 to move downwardly inaccordance with the downward motion of the propulsion component 315.

As mentioned above, the control leg 313 may be associated with the motorassembly 322. In some embodiments, the motor assembly 322 may be coupledbetween the upper four-bar link 325 and the lower four-bar link 327 andthe propulsion component 315. As shown in the perspective view 331 inFIG. 3A, the motor assembly 322 optionally comprises a steering actuator324 and a wheel actuator 326. As shown, the upper four-bar link 325 ofthe control leg 313 may be associated with (e.g., coupled to) thesteering actuator 324, and the lower-four bar link 327 may be associatedwith (e.g., coupled to) the wheel actuator 326. In some embodiments, thesteering actuator 324 is optionally configured to cause a firstpropulsion-producing movement of the propulsion component 315 coupled tothe control leg 313 associated with the steering actuator 324. Forexample, the steering actuator 324 is configured to cause the propulsioncomponent 315 to revolve/spin (e.g., a yaw rotational motion about avertical axis through a center of the propulsion component) to steer thepropulsion component 315 (e.g., cause the wheel to turn left or right).In some embodiments, the wheel actuator 326 is configured to cause asecond propulsion-producing movement of the propulsion component 315coupled to the control leg 313 associated with the wheel actuator 326.For example, the wheel actuator 326 is configured to cause thepropulsion component to rotate (e.g., a pitch rotational motion about anaxis perpendicular to the a center of the propulsion component) to drivethe propulsion component 315 (e.g., cause the wheel to accelerate,decelerate, coast, etc.).

As discussed herein, the suspension system 310 of the control leg 313may enable the control leg 313 to be selectively raised and/or loweredwith respect to the chassis of the rover and/or the surface on which therover is operating. As shown in FIG. 3B, the suspension system 310 maycomprise a rocker arm 335 disposed within the lower compartment 321B ofthe chassis portion of control leg 313. As shown, in some embodiments, afirst portion of the rocker arm 335 may be coupled to a rocker shaft333, which optionally includes a spring 336. In some embodiments, thespring 336 may have a predefined rate or spring constant chosen forresisting a change in orientation of the rocker arm 335, which will bediscussed in more detail later. In some embodiments, the rocker arm 335may comprise a rocker angular encoder (e.g., resolver) 339, as shown inFIG. 3B. In some embodiments, a second portion of the rocker arm 335 maybe coupled to a linear actuator 337, which optionally includes acommutator angular encoder (e.g., resolver) (not shown). As shown inFIG. 3B, in some embodiments, the linear actuator 337 may also include apin/rod 338 extending a length between a first portion of the linearactuator 337 and a second portion of the linear actuator 337. In someembodiments, the linear actuator 337 may be a screw/thread basedactuator configured to increase a length of the rod 338 that is betweenthe first portion and the second portion of the linear actuator 337. Insome embodiments, the suspension system 310 may comprise a yoke coupling340 coupled between the second portion of the linear actuator 337 andthe first coupling 329. In some embodiments, as discussed in more detailbelow, the yoke coupling 340 and the first coupling 329 move togethersynchronously (e.g., are fixed with respect to the other). As shown inFIG. 3B, in some embodiments, the first coupling 329 may include a linkangular encoder (e.g., resolver) 341.

In some embodiments, the suspension system 310 may be provided with oneor more supporting components within the lower compartment 321B ofcontrol leg 313. For example, the suspension system 310 may be providedwith a rocker bump stop 332 disposed above the rocker arm 335 in FIG.3B. In some embodiments, the rocker bump stop 332 may limit a rotationof the rocker arm 335 to protect the rocker arm 335 from potentialcollisions with components above the rocker arm (e.g., collisions withcomponents of the latching system 306, which could damage the rocker arm335, for example). The suspension system 310 may also be provided with aleg bump stop 334 disposed above the upper four-bar link 325. The legbump stop 334 may be positioned (at least partially) external to thelower compartment 321B, such that an upward movement of the upperfour-bar link 325 is prevented from causing the upper four-bar link 325to collide with the exterior portion of the chassis, which could damagethe upper four-bar link 325 and/or the first coupling 329 and yokecoupling 340.

As mentioned above, the various components of the suspension system 310may be disposed and contained within the chassis portion of control leg313 (e.g., within lower compartment 321B) for dust mitigation. Forexample, as shown in FIG. 3B, housing the suspension system 310 withinthe chassis portion creates a boundary (e.g., represented by dashedlines) 342 between the exterior of the rover and the various componentsof the suspension system 310. The boundary 342 may prevent dust, soil,and other substances (e.g., lunar substances) from entering the interiorof the chassis and contacting and building up on or near the suspensionsystem components, which thus advantageously maintains system integrityand prolongs system life.

As outlined above, the various components of the suspension system 310are communicatively linked (e.g., via physical connections), such thatthe components may be configured to move and function fluidly via achain of interconnected motion. In some embodiments, the rover ECU(e.g., corresponding to ECU 104 in FIGS. 1A-1B) may be in communicationwith the linear actuator 337 (including the commutator resolver (notshown)), the rocker resolver 339, and the link resolver 341. It shouldbe understood that, while not explicitly shown, the ECU may communicatewith the linear actuator 337, the rocker resolver 339, and the linkresolver 341 via any suitable communication means (e.g., wired orwireless communication means). As described below, the ECU may beconfigured to determine and evaluate a plurality of suspension systemparameters for operating the rover to perform one or more suspensionfunctions.

FIG. 3C illustrates examples of the plurality of suspension systemparameters that may be computed and evaluated based on angular encoder(e.g., resolver) readings. As mentioned above, the ECU may be incommunication with the rocker resolver 339 and the link resolver 341. Insome embodiments, the rocker resolver 339 and/or the link resolver 341may be rotary transformers configured to measure degrees of rotation.For example, the rocker resolver 339 may measure degrees of rotation ofthe rocker arm 335, and the link resolver 341 may measure degrees ofrotation of the first coupling 329 (and thus the upper four-bar link 325coupled to the first coupling 329).

As mentioned above with reference to FIGS. 3B, in some embodiments, afirst end of the rocker shaft 333 may be coupled to the rocker arm 335.In some embodiments, a second end of the rocker shaft 333 is optionallyanchored to a respective location within the chassis portion (i.e., thelower compartment 321 b in FIG. 3B) of control leg 313. In one or moreembodiments, the rocker shaft 333 is optionally anchored to a respectivelocation adjacent to the linear actuator 337, as shown in FIG. 3C, suchthat an orientation of the rocker shaft 333 (and spring 336) issubstantially vertical with respect to the reference. In one or moreembodiments, the second end of the rocker shaft 333 is optionallyanchored to a respective location adjacent to the rocker arm 335, asshown in FIG. 5B, for example, such that an orientation of the rockershaft 333 is substantially horizontal with respect to the top surface ofthe chassis. Additionally or alternatively, in some embodiments, theorientation of the rocker shaft 333 may be evaluated with respect to thesurface on which the rover is placed. Additionally or alternatively, insome embodiments, the orientation of the rocker shaft 333 may beevaluated with respect to a respective orientation of linear actuator337. In FIG. 3C, a first end of the rocker shaft 333 is coupled to thefirst portion of the rocker arm 335 via a first fastener 345 a, and asecond end of the rocker shaft 333 is anchored to the respectivelocation via a second faster 345 b (e.g., a bolt, screw, pin, or anysuitable fastener). Similarly, a first end of the linear actuator 337 iscoupled to the second portion of the rocker arm 335 via a third fastener347 a (e.g., a bolt, screw, pin, or any suitable fastener), and a secondend of the linear actuator 337 is coupled to the yolk coupling 340 via afourth fastener 347 b (e.g., a bolt, screw, pin, or any suitablefastener).

In some embodiments, the fasteners discussed above may provide pivotand/or anchor points about which various components of suspension system310 may or may not be configured to rotate and/or move. In someexamples, in FIG. 3C, the first fastener 345 a, which couples the firstend of the rocker shaft 333 to the first portion of the rocker arm 335,may provide a pivot point between the rocker shaft 333 and the rockerarm 335. The second fastener 345 b may fix the second end of the rockershaft 333 to the respective location within the lower compartment of thecontrol leg 313 (e.g., and thus prevents movement of the rocker shaft333 about the second fastener 345 b). In some examples, the thirdfastener 347 a, which couples the first end of the linear actuator 337to the second portion of the rocker arm 335, may provide a pivot pointbetween the linear actuator 337 and the rocker arm 335. In someexamples, the fourth fastener 347 b, which couples the second end of thelinear actuator 337 to the yoke coupling 340, may provide a pivot pointbetween the linear actuator 337 and the yoke coupling 340 (e.g., andthus the first coupling 329 and the upper four-bar link 325 coupled tothe first coupling 329).

In some embodiments, the plurality of suspension parameters may includeeffective lengths, which are defined as between respective fastenerscoupled to the rocker shaft 333 and the linear actuator 337. Forexample, as shown in FIG. 3C, a first effective length L1 may be definedbetween the first fastener 345 a, which couples the first end of therocker shaft 333 to the rocker arm 335, and the second fastener 345 b,which anchors the second end of the rocker shaft within the chassisportion of control leg 313. In some embodiments, the first effectivelength L1 may be a known value for a given orientation of the rocker arm335 (e.g., for a level rocker arm, in which the rocker shaft 333 isfully or substantially extended). A second effective length L2 may bedefined between the third fastener 347 a, which couples the first end ofthe linear actuator to the rocker arm 335, and the fourth fastener 347b, which couples the second end of the linear actuator to the yokecoupling 340. In some embodiments, the second effective length L2 may bea known value for a given length of the linear actuator pin 338. Asdescribed in more detail later, the first effective length L1 may change(e.g., increase or decrease) in response to a change in orientation ofthe rocker arm 335. The second effective length L2 may change inresponse to a change in a length of the linear actuator pin 338. In someembodiments, the length of the linear actuator pin 338 changes inresponse to operation of the linear actuator 337, as discussed in moredetail later.

In some embodiments, the plurality of suspension parameters may includeangular encoder (e.g., resolver) angles, which are measured using therocker resolver 339 and the link resolver 341. For example, as shown inFIG. 3C, a first resolver angle, θ_(R), may be measured using the rockerresolver 339. The first resolver angle is optionally an angle ofrotation of the rocker arm 335 measured with respect to the reference(e.g., the surface on which the rover is configured to be placed, and/orthe pivot point at which the rocker arm 335 is coupled to the chassis(e.g., via second fastener 345 b coupling the rocker shaft 333 to thechassis)). As such, when the rocker arm 335 is in a first respectiveorientation (e.g., when the surface on which the rover is placed isflat), the first resolver angle is effectively zero (“0”), as shown inFIG. 3C. A change in the first effective length L1 (e.g., due to achange in the length of the rocker shaft 333) optionally corresponds toa rotation in the rocker arm 335 with respect to the reference above,and thus changes the value of the first resolver angle. A secondresolver angle, θ_(H), may be measured using the link resolver 341. Thesecond resolver angle is optionally an angle of rotation of the firstcoupling 329 (and thus the upper four-bar link 325 coupled to the firstcoupling 329) measured with respect to the reference. As such, when thefirst coupling 329 is in a first respective orientation (e.g., when thesurface on which the rover is placed is flat), the second resolver angleis effectively zero, as shown in FIG. 3C. A change in the secondeffective length L2 (e.g., due to a change in the length of the linearactuator pin 338) optionally corresponds to a rotation in the firstcoupling 329 with respect to the reference, and thus changes the valueof the second resolver angle (e.g., to have a value of “X”), as shown.

Accordingly, in some embodiments, the rover ECU may compute theplurality of suspension parameters using the rocker resolver 339 and thelink resolver 341, and the known distances of the first effective lengthL1 and the second effective length L2 at respective orientations of therocker arm 335 and the first coupling 329, respectively. As discussed inmore detail with reference to FIGS. 5A-6B, computation of theabove-described plurality of suspension parameters may enable the roverto be operated to retrieve, transport, and/or deposit modular payloads,as well as adapt to unevenness in the terrain during suchtransportation.

FIG. 4 illustrates examples of modular payloads 452 a-452 b configuredto be retrieved, transported, and/or deposited by a rover according tosome embodiments of the disclosure. The modular payloads 452 a-452 bshown in FIG. 4 are examples of payloads that may need to be transportedon planetary surfaces (e.g., the surface of a moon). As shown, themodular payloads may be cuboidal in shape, and may vary in size (e.g.,volume), depending on the number, size, type, fragility, etc. of thecontents of the payloads.

In some embodiments, the modular payloads 452 a-452 b may each comprisea plurality of latch receptacles 454. As shown in FIG. 4 , the pluralityof latch receptacles 454 may be disposed along one or more sides of eachof the modular payloads 452-452 b. For example, the plurality of latchreceptacles 454 may be provided along one side, two sides, or threesides of each of the modular payloads 452 a-452 b. In some embodiments,the plurality of latch receptacles 454 may be located within the upper1, 2, 3, 5, 10, 20, 30 or 50 percent of the height dimension of themodular payloads 452 a-452 b. In some embodiments, a number of theplurality of latch receptacles 454 provided may vary depending on thesize (e.g., depending on the length and/or width) of the modularpayload. For example, the first modular payload 452 a optionallyincludes the dimensions of 1.5 m×1.5 m×1 m, and is provided with sixlatch receptacles (e.g., three latch receptacles disposed along bothsides of the modular payload 452 a). The second modular payload 452 boptionally includes the dimensions of 1.5 m×2 m×1 m, and is providedwith eight latch receptacles (e.g., four latch receptacles disposedalong both sides of the modular payload 452 b).

Conventionally, few mobility platforms exist for the deposition and/ortransportation of modular payloads on planetary surfaces (e.g., thesurface of a moon). For example, with current technologies, modularpayloads, such as those shown in FIG. 4 , may be deposited on thesurface of the Moon after landing (e.g., by a crane on a planetarylander) and then manually transported over the lunar surface (e.g.,manually carried and/or lifted onto a lunar rover vehicle andsubsequently driven) by a user (e.g., an astronaut). Moreover, thepayloads may have to be transported serially, exhausting time andresources that could be better spent towards exploration, scientificsample collection, construction, or other lunar mission objectives.Thus, there is a need for providing a single mobility platformconfigured to autonomously retrieve, transport, and deposit such modularpayloads without the need for direct user input or intervention.

Accordingly, as described herein, the rover latching system (e.g.,corresponding to latching system 106 in FIGS. 1A-1B) may correspond tothe plurality of latch receptacles 454 of the modular payloads 452 a-452b. In some embodiments, the plurality of latch receptacles 454 areoptionally configured to (e.g., shaped to) receive (e.g., become latchedwith) a corresponding plurality of latches of the rover latching system,which will be described in more detail with respect to FIGS. 5F-5H. Forexample, as discussed in more detail with reference to FIGS. 5F-5H, therover latching system may be configured to interface with the pluralityof latch receptacles 454, thus having a configuration of latchreceptacles corresponding to the number of the plurality of latchreceptacles and the distance between respective pairs of latchreceptacles of the plurality of latch receptacles. In some suchembodiments, when the plurality of latch receptacles 454 become latchedwith the plurality of latches, the modular payload becomes attached tothe chassis of the rover.

Rover Retrieval, Transportation, and/or Deposition of Payloads

Attention is now directed towards example operations of the rover inretrieving a respective modular payload for the subsequenttransportation and/or deposition of the respective modular payload. Therespective modular payload may be located at a respective location on aplanetary surface (e.g., the surface of a moon) which, for ease ofillustration and explanation, is an even (e.g., substantially flat)location on the planetary surface. As described previously herein, thevarious autonomous operations of the systems of the rover describedbelow may be (at least substantially) controlled by the rover ECU.

FIGS. 5A-5H illustrate an example of autonomous retrieval of a modularpayload 552 using a rover 502 according to some embodiments of thedisclosure. In some embodiments, the rover 502 optionally corresponds torover 202 shown in FIGS. 2A-2B, and modular payload 552 optionallycorresponds to modular payload 452 shown in FIG. 4 . In someembodiments, the rover 502 may, via the one or more sensors 520, detectand identify a location of the modular payload 552 on the lunar surface.As shown in FIG. 5A, after identifying the location of the modularpayload 552, the rover 502 may be operated (e.g., via the rover ECU) toautonomously approach the modular payload 552. For example, the ECU maydrive the plurality of propulsion components 515 (e.g., using the motorassembly (e.g., corresponding to motor assembly 322 in FIG. 3A)associated with each propulsion component) to drive the rover 502 towardthe modular payload 552.

As discussed above with reference to FIG. 4 , the modular payload 552may comprise a plurality of latch receptacles 554 disposed along twosides of the modular payload 552 (e.g., along a first side of themodular payload 552 and along a second side, opposite the first side),as shown in FIG. 5A. As the rover 502 is driven toward the modularpayload 552, the ECU may utilize data (e.g., image data) captured viathe one or more sensors 520 to position the interior 501 of the chassis503 around the modular payload 552. Particularly, as discussed below,the rover 502 may position itself above the modular payload 552 toretrieve the modular payload 552.

As shown in FIG. 5B, when the rover 502 is positioned above the modularpayload 552, the plurality of propulsion components 515 optionallyceases to be driven, such that the rover 502 remains stationary abovethe modular payload 552. In some embodiments, the rover 502 may ceasedriving forward when the rover 502 detects that all or a substantialportion (e.g., a threshold amount of a top surface (e.g., for a 1.5 m×2m×1 m modular payload, the threshold amount is equal to an area of thetop surface, defined by 1.5 m×2 m)) of the modular payload 552 ispositioned below the rover 502. In some embodiments, the modular payload552 comprises a plurality of conical protrusions 585. Referring back toFIG. 5A, the plurality of conical protrusions 585 may be positioned onthe top surface of the modular payload 552, wherein a first end of arespective conical protrusion 585 is coupled to the top surface of themodular payload 552 and a second, smaller end of the respective conicalprotrusion 585 is pointed upward and away from the top surface of themodular payload 552. In some embodiments, the rover 502 may comprise aplurality of conic recessions (not shown) configured to receive theplurality of conic protrusions 585. For example, the plurality of conicrecessions (not shown) may be disposed in an interior portion (e.g., theunderside) of the medial portion 507 of the chassis 503 of the rover502. In some embodiments, the rover 502 may utilize sensor data capturedvia the one or more sensors 520 to position the plurality of conicrecessions (not shown) above the plurality of conic protrusions 585, asshown in FIG. 5B. In some embodiments, the plurality of conic recessions(not shown) of the rover 502 may comprise proximity sensors configuredto detect a presence of the plurality of conic protrusions 585 when theplurality of conic protrusions 585 enter the plurality of conicrecessions of the rover 502.

As shown in the detailed view in FIG. 5B, the rover 502 comprises thesuspension system 510 (e.g., corresponding to suspension system 310 inFIGS. 3A-3B) within the chassis 503. As discussed above with referenceto FIGS. 3A-3C, the suspension system 510 may include the rocker shaft533 (including the spring), the rocker arm 535, and the linear actuator537 including the pin 538. In some embodiments, when the rover 502 ispositioned above the modular payload 552, the suspension system 510 ofeach control leg (e.g., corresponding to control leg 313 in FIGS. 3A-3C)may be operated (e.g., by the rover ECU) to initiate the process ofretrieving the modular payload 552. Particularly, the linear actuator537 may be operated to cause a lengthening of the pin 538 (e.g., withrespect to the yoke coupling 540) to increase the second effectivelength (e.g., L2 in FIG. 3C) and thus lower the chassis 503 with respectto a reference (e.g., the surface on which the rover 502 is placed, or apoint or plane on/along a bottom surface of the chassis 503) and towardthe top surface of the modular payload 552, as discussed below.

As shown in FIG. 5C, as a portion of the pin 538 that is between thelinear actuator 537 and the yoke coupling 540 increases for each controlleg of the rover 502, the chassis 503 of the rover 502 is lowered withrespect to the reference (e.g., the surface on which the rover 502 isplaced) and thus oriented closer toward the top surface of the modularpayload 552. In some embodiments, as the second effective length L2increases (e.g., as the distance between the linear actuator 537 and theyoke coupling 540 increases), a respective orientation of the upperfour-bar link 525 and a respective orientation of the lower four-barlink 527 changes for each control leg of the rover 502. Referring backto FIGS. 3A-3C, the linear actuator 337 may be operated to cause arotation (e.g., yaw rotational motion in a first respective direction(e.g., counterclockwise direction)) of the rod 338 coupled between thefirst portion of the linear actuator 337 and the second portion of thelinear actuator. As the rod 338 is rotated, for example, the portion ofthe rod 338 that is between the yoke coupling 340 and the linearactuator 337 may increase in length. As mentioned above, the spring 336of the rocker shaft 333 optionally has a respective spring rate, whichmay enable the rocker arm 335 to resist moving (e.g., resist pitchrotational motion about the third fastener 347 a) as the linear actuator337 moves (e.g., in response to driving the rod 338). For example, thespring 336 may retain the rocker shaft 333 at a lengthened position(e.g., such that the first effective length L1, defined by the distancebetween the first fastener 345 a and the second fastener 345 b, does notchange), as shown in FIG. 3B, and thus maintains the rocker arm 335 at aresting position (e.g., wherein the first resolver angle θ_(R), is about0 degrees (as measured by the rocker resolver 339)). The increase in theportion of the rod 338 optionally causes the second effective length L2to increase. As described above, the second effective length may bedefined between the third fastener 347 a and the fourth fastener 347 b.As the second effective length L2 increases, the yoke coupling 340 maypivot (e.g., pitch rotational motion in a clockwise direction) about thefourth fastener 347 b. The rotation of the yoke coupling 340 optionallycauses the first coupling 329 coupled to the yoke coupling 329 to rotate(e.g., pitch rotational motion in a clockwise direction) in accordancewith the rotation of the yoke coupling 340. The rotation of the firstcoupling 329 may then cause the upper four-bar link 325 coupled to thefirst coupling 329 to be raised with respect to the surface on which therover is placed, which subsequently causes the lower four-bar link 327to be raised (e.g., and to pivot (e.g., pitch rotational motion in aclockwise direction) about the second coupling 330) and thus causes thechassis of the rover to be lowered with respect to the surface on whichthe rover is placed.

For example, from FIG. 5B to FIG. 5C, in response to the increase in thedistance between the linear actuator 537 and the yoke coupling 540, theupper four-bar link 525 and the lower four-bar link 527 are each changedfrom having a first orientation (e.g., tilted downward) with respect tothe reference to having a second orientation (e.g., being substantiallylevel) with respect to the reference (e.g., the surface on which therover is placed or a point or plane on/along the bottom surface of thechassis 503). Additionally, for example, as discussed previously withreference to FIG. 3C, the second resolver angle, θ_(H), measured usingthe link resolver 341 optionally also changes. For example, before thechassis 503 begins lowering toward the top surface of the modularpayload 552, the second resolver angle may be a first angle (e.g., 0degrees) with respect to the surface on which the rover 502 is placed.As the upper four-bar link 325 is changed from having the firstorientation to having the second orientation, the first coupling 329changes from having the first orientation to the second orientation. Thechange in orientation of the first coupling 329 causes the secondresolver angle to change from being the first angle to being a secondangle (e.g., 10, 15, 20, 30, 40, 50, 60, etc. degrees) with respect tothe surface on which the rover 502 is placed. The changes in orientationof each of the upper four-bar links 525 and the lower four-bar links 527with respect to the reference cause the chassis 503 of the rover 502 tolower with respect to the reference. From FIG. 5C to FIG. 5D, as theeffective length of the pin 538 continues to increase, the respectiveorientations of the upper four-bar link 525 and the lower four-bar link527 (e.g., and thus the respective angle of the second resolver angle,θ_(H), of the first coupling 329) of each of the control legs continueto change in accordance with the increase of the effective length, whichcauses the chassis 503 of the rover 502 to continue to be lowered, asshown.

As shown in FIG. 5E, the effective length of the pin 538 of each controlleg may be increased until the (e.g., bottom surface of the medialmember of the) chassis 503 of the rover 502 is lowered close enough tothe top surface of the modular payload 552 to retrieve the modularpayload 552. For example, as discussed previously with reference to FIG.3C, the rover ECU may be configured to compute a respective angle of theyoke coupling 540 and the upper four-bar link 525 with respect to thereference using the link angular encoder (e.g., link resolver 341). Insome embodiments, when the computed respective angle corresponds arelative threshold angle (e.g., relative to the size of the modularpayload, where the threshold angle is 30 degrees, 35 degrees, 45degrees, 50 degrees, 60 degrees, 65 degrees, 70 degrees, etc.) withrespect to the reference, the rover ECU may cease operating the linearactuator 537, such that the effective length of the pin 538 no longerincreases and respective orientations of the upper four-bar link 525 andthe lower four-bar link 527 of each control leg no longer change. Forexample, different sized modular payloads will have associated angles atwhich the rover 502 may stop lowering to retrieve the modular payloads.A taller modular payload (e.g., a payload having a greater heightdimension than that shown in FIGS. 5A-5H) may require the rover 502 tostop lowering at a first relative threshold angle that is smaller than asecond relative threshold angle that may be required for retrieving ashorter modular payload (e.g., a payload having a smaller heightdimension than that shown in FIGS. 5A-5H).

In some embodiments, when the chassis 503 of the rover 502 has beenlowered with respect to the reference to a respective elevation abovethe top surface of the modular payload 552 (e.g., abutting the topsurface of the modular payload 552 or within 2 cm, 5 cm, 7 cm, 10 cm, 15cm, etc. above the top surface of the modular payload 552) to at leastpartially surround the modular payload 552 such that the plurality ofconic protrusions 585 of the rover 502 in FIG. 5A have entered theplurality of conic recessions (not shown) of the modular payload 552,the rover ECU may initiate one or more latching operations for retrievalof the modular payload 552. FIGS. 5F-5H illustrate an example of therover latch system 506 and methods thereof. In some embodiments, therover latch system 506 optionally corresponds to the latch system 206shown in FIG. 2B.

As shown in FIG. 5F, the rover latch system 506 may be disposed withinthe chassis 503, as similarly described previously with reference toFIG. 2B. In some embodiments, the rover latch system 506 may be disposedwithin respective halves of the rover chassis 503 (e.g., a front halfand a rear half), as shown in FIG. 5F. In some embodiments, the roverlatch system 506 (e.g., for a respective half of the rover chassis 503)may comprise a plurality of hooks/appendages 553. In some embodiments,the plurality of hooks 553 may be housed within cavities of respectivesides of the chassis 503 (e.g., within the first side 205 and the secondside 209 in FIGS. 2A-2B) and may be configured to protrude outwardlyfrom within the respective sides of the chassis 503 to engage with theplurality of latch receptacles 554 of the modular payload 552. In someembodiments, the plurality of hooks 553 may be configured to accommodatevarious possible shapes or arrangements that the plurality of latchreceptacles may be provided in. The rover 502 may thus be configured toretrieve any payload comprising a plurality of latch receptacles so longas the payload fits within the interior 511 of the rover chassis 503. Insome embodiments, the plurality of hooks/latches 553 may be coupled to aplurality of shafts 557 disposed in the upper portions of the sides ofthe chassis 503 (e.g., within the upper compartment 221A in FIG. 2B). InFIG. 5F, the latch system 506 for the front half of the chassis 503 maycomprise two shafts 557 each coupled to two hooks 553. In someembodiments, the plurality of shafts 557 may be coupled to acorresponding plurality of connecting devices (e.g., cables, pins,wires, etc.) 556 disposed within the medial member of the chassis 503(e.g., within the medial member 207 in FIG. 2B). As shown, each shaft557 may be coupled to a corresponding connecting device 556 within thechassis 503. In some embodiments, each shaft 557 of the plurality ofshafts may be coupled at a first end of the shaft to a given connectingdevice 556 via connection element 558 that extends radially from thefirst end of the shaft 557. In some embodiments, the connection element558 may be configured to cause a rotation (e.g., roll rotational motion)of the shaft 557 coupled to the connection element 558.

In some embodiments, the latch system 506 optionally comprises one ormore motors 555 coupled to the plurality of connecting devices 556. Insome embodiments, each connecting device 556 of the plurality ofconnecting devices may be coupled to a respective motor 555 via a rotaryelement 548. In some embodiments, the rotary element 548 may beconfigured to be rotated (e.g., roll rotational motion) by therespective motor 555 to cause a translation of the plurality ofconnecting devices 556 coupled to the rotary element 548.

In some embodiments, the one or more motors 555 of the latch system 506may be configured to selectively drive the protrusion of the pluralityof hooks 553 to engage with the plurality of latch receptacles 554 ofthe modular payload 552. For example, as shown in FIG. 5F, the pluralityof connecting devices 556 coupled to the motor 555 may be arranged in afirst respective orientation, which optionally causes the plurality ofhooks 553 to be positioned within the chassis 503. The motor 555 may beoperated (e.g., by the rover ECU) to change the orientation of theplurality of connecting devices 556, which optionally causes theplurality of hooks 553 to protrude radially from within the chassis 503.

As shown in FIG. 5G, the motor 555 may be operated to cause theplurality of hooks to engage with the corresponding plurality of latchreceptacles 554 of the modular payload 552. In some embodiments, themotor 555 (e.g., which may be a rotary motor) may change the orientationof the plurality of connecting devices 556 (e.g., by translating theplurality of connecting devices 556 in a respective direction (e.g.,outward)). For example, from FIG. 5F to FIG. 5G, the motor 555 may beoperated to cause the rotary element 548 to rotate (e.g., rollrotational motion about an axis perpendicular to the motor 555) toproduce a translation in the orientation of the plurality of connectingdevices 556 (e.g., with respect to the reference (e.g., the surface onwhich the rover is placed, or the top surface of the modular payload552)) from the first orientation to a second orientation (e.g., aparallel orientation with respect to the reference). In response to thechange in orientation of the plurality of connecting devices 556, theplurality of shafts 557 may rotate in a respective direction (e.g.,counterclockwise rotation of the front-right shaft 557) to cause theplurality of hooks to protrude radially toward and engage with theplurality of latch receptacles 554. For example, the translation of theplurality of connecting devices 556 may cause the connection element 558coupled to a second end of each connecting device 556 to rotate (e.g.,roll rotational motion in a respective direction away from the motor555). The rotational motion of the connection element 558 may produce acorresponding rotation (e.g., roll rotational motion in the respectivedirection) of the shaft 557 coupled to the connection element (e.g., atthe first end of the shaft 557). The shaft 557 may be coupled within thechassis of the rover to enable the shaft 557 to rotate around an axisextending through a middle of and along a length of the shaft 557 inresponse to the change in the pivot angle between the radially extendedconnection element 558 and the connecting device 556 coupled to theconnection element 558. The hooks 553 fixedly coupled to opposite endsof the shaft 557 may then radially protrude (e.g., in accordance withthe roll rotational motion of the shaft 557) to engage with thecorresponding latch receptacles 554 of the modular payload 552.

For example, in the sectional view of FIG. 5H, a first connecting device556 a coupled to the motor 555 may be in the first orientation, suchthat a first hook 553 a is positioned within (e.g., a cavity of) thechassis 503 (e.g., disengaged from a first latch receptacle 554 a). Whenthe motor 555 is operated to initiate latching with the modular payload552 (e.g., causes a rotation of the rotary element 548 discussed above),the plurality of connecting devices may be changed from the firstorientation to the second orientation, as shown by a second connectingdevice 556 b. In the second orientation, the second connecting device556 b optionally causes a rotation of the connection element 558 bcoupled to the second connecting device 556 b (e.g., in a direction awayfrom the motor 555). The rotation of the connection element 558 b maycause a rotation (e.g., roll rotational motion in the direction awayfrom the motor 555) of a respective shaft 557 b, which causes a secondhook 553 b to protrude outwardly from the chassis 503 and engage withthe corresponding latch receptacle 554 b of the modular payload 552. Insome embodiments, a first portion of the second hook 553 b remainswithin the cavity of the chassis 503 and a second portion of the secondhook 553 b protrudes from the cavity of the chassis 503 when the motor555 is operated.

It should be understood that, in some embodiments, the first connectingdevice 556 a and the second connecting device 556 b will changeorientation together, because the first connecting device 556 a and thesecond connecting device 556 b are both coupled to the same rotatingelement driven by the motor 555. FIG. 5H illustrates the two states ofthe first connecting device 556 a and the second connecting device 556 bindependently for ease of description and comparison.

Thus, as outlined above, the rover 502 may be autonomously operated tolocate, approach, and retrieve a modular payload for subsequenttransportation and/or deposition of the modular payload at a respectivelocation on the lunar surface. As discussed above, the retrieval of themodular payload according to the above example processes provides for aninput-free, effective, and long-lasting mobility platform which maygreatly reduce time and resources spent manually loading, transporting,and unloading payloads. Further, as an advantage, efforts and resourcesmay be focused and allocated toward more significant and/or specializedlunar mission objectives in which human input may be required, such asexploration, testing, construction and the like.

In some embodiments, following the retrieval of the modular payload 552,the rover ECU may initiate processes for transporting and/or depositingthe modular payload 552. For example, the linear actuator 537 may beoperated to decrease the effective length of the pin 538, which maychange respective orientations of the upper four-bar link 525 and thelower four-bar link 527 of each control leg to gradually raise thechassis 503 of the rover 502 and the modular payload 552 attached to thechassis 503 with respect to the surface. Referring back to FIGS. 3A-3C,the linear actuator 337 may be operated to cause a rotation (e.g., yawrotational motion in a second respective direction (e.g., pitchrotational motion in a clockwise direction)) of the rod 338 coupledbetween the first portion of the linear actuator 337 and the secondportion of the linear actuator. As the rod 338 is rotated, for example,the portion of the rod 338 that is between the yoke coupling 340 and thelinear actuator 337 may decrease in length. As mentioned above, thespring 336 of the rocker shaft 333 optionally has a respective springrate, which may enable the rocker arm 335 to resist moving (e.g., resistpitch rotational motion about the third fastener 347 a) as the linearactuator 337 moves (e.g., in response to driving the rod 338). Forexample, the spring 336 may retain the rocker shaft 333 at a lengthenedposition (e.g., such that the first effective length L1, defined by thedistance between the first fastener 345 a and the second fastener 345 b,does not change), as shown in FIG. 3B, and thus maintains the rocker arm335 at a resting position (e.g., wherein the first resolver angle θ_(R),is about 0 degrees (as measured by the rocker resolver 339)). Thedecrease in the portion of the rod 338 optionally causes the secondeffective length L2 to decrease. As described above, the secondeffective length may be defined between the third fastener 347 a and thefourth fastener 347 b. As the second effective length L2 decreases, theyoke coupling 340 may pivot (e.g., rotational motion in acounterclockwise direction) about the fourth fastener 347 b. Therotation of the yoke coupling 340 optionally causes the first coupling329 coupled to the yoke coupling 329 to rotate (e.g., rotational motionin a counterclockwise direction) in accordance with the rotation of theyoke coupling 340. The rotation of the first coupling 329 may then causethe upper four-bar link 325 coupled to the first coupling 329 to belowered with respect to the surface on which the rover is placed, whichsubsequently causes the lower four-bar link 327 to be lowered (e.g., andto pivot (e.g., rotational motion in a counterclockwise direction) aboutthe second coupling 330) and thus causes the chassis of the rover to beraised with respect to the surface on which the rover is placed.

In some embodiments, the plurality of propulsion components 515 of therover 502 may be driven (e.g., by a corresponding motor assembly) totransport the rover 502 and the modular payload 552 to a respectivelocation on the surface while the chassis 503 is in the raised position(e.g., the position of chassis 503 in FIG. 5A). At the respectivelocation, the chassis 503 of the rover 502 may again be lowered withrespect to the lunar surface (e.g., according to the example processesdescribed above), and the motor 555 may be actuated to cause theplurality of hooks to disengage from the plurality of latch receptacles554 of the modular payload 552, thereby depositing the modular payloadat the respective location. The rover 502 may then proceed to retrievinga second modular payload or performing another action as instructed bythe rover ECU (e.g., returning to a lunar outpost or lander).

FIGS. 6A-6B illustrate an example of the adaptive suspension of a rover602 during autonomous transport of a modular payload 652 according tosome embodiments of the disclosure. In some embodiments, the rover 602optionally corresponds to rovers 502 and/or 202 shown in FIGS. 5A-5Hand/or FIGS. 2A-2B, respectively. As described above, the rover 602 mayautonomously transport the modular payload 652 after retrieval of themodular payload 652 from a respective location on the lunar surface. Asmentioned above with reference to FIGS. 5A-5H, the modular payload 652may be located at a respective location that is (substantially) flat. Asdiscussed below, during the autonomous transportation of the modularpayload 652, the rover 602 may encounter one or more occurrences ofunevenness on the lunar surface. In some embodiments, the suspensionsystem of the rover 602 may be configured to adapt to such occurrencesof unevenness during transport, such that the chassis 603 and thus themodular payload 652 may remain substantially level with respect to thelunar surface.

As shown in FIG. 6A, the rover 602 may be transporting the modularpayload 652 over the lunar surface 659. For example, in FIG. 6A, theplurality of propulsion components 615 are each being driven by acorresponding motor assembly (e.g., motor assembly 322 in FIG. 3A) todrive the rover 602 across the lunar surface 659. As shown in FIG. 6A,the plurality of control legs 613 may be positioned in an uprightposition (e.g., as shown similarly in FIGS. 5A-5B) to maintain a groundclearance for a bottom surface of the modular payload 652 duringtransportation. As mentioned above, the lunar surface may includeunevenness (e.g., obstacles or hindrances to travel, such as rocks,dips, craters, etc.). For extreme instances of unevenness, such as deepcraters, the rover ECU may be configured to detect a respective craterusing the one or more sensors 620, and operate the plurality ofpropulsion components 615 to steer the rover 602 away from therespective crater and avoid potential damage to the rover 602 and/or themodular payload 652 and its contents.

In some instances, the rover 602 may be unable to avoid unevenness inthe lunar surface 659. For example, the lunar surface 659 contains vaststretches of unevenness and the only path to a respective destinationmay be through the portions of unevenness. In such instances, the rovermay be configured to autonomously adapt to the unevenness in the lunarsurface 659 and maintain a ground clearance between the bottom surfaceof the modular payload 652 and the lunar surface 659 to prevent and/orsignificantly reduce potential collisions between the modular payload652 and the lunar surface 659.

As shown in FIG. 6B, in some instances, the lunar surface 659 mayinclude unevenness, such as bumps 661 and/or dips 662. In someembodiments, the rover suspension system may be controllable to operateaccording to a selected mode. In some embodiments, the rover suspensionsystem may be controllable to operate according to a passive suspensionmode or one or more active suspension modes.

For example, referring back to FIGS. 3B-3C, in the passive suspensionmode, the rover ECU forgoes operation of the components of thesuspension system 310. In some embodiments, while the rover 602transports the respective payload 652 and while employing passivesuspension, the rocker shaft 333 and spring 336 may dampen shocks to agiven control leg 313 that may be induced by contacts between a givenpropulsion component and a bump or dip in the lunar terrain 659. Forexample, as described previously with respect to FIG. 3B, the spring 336may have a rate/constant that enables the spring 336 to resist anddeflect shocks to the given control leg 313. When a given propulsioncomponent contacts unevenness in the terrain 659, such as a bump 661 ora dip 662, a shock may be absorbed by the given propulsion component inresponse to contacting the bump 661 or the dip 662. The shock maypropagate (e.g., via a vibration of the propulsion component) throughthe control leg (e.g., through the upper four-bar link 325 and/or thelower four-bar link 327), and transfer to the components of thesuspension system 310. For example, referring back to FIGS. 3A-3C, whenthe propulsion component 315 contacts the bump 661, the shock pulse(s)may travel from the upper four-bar link 325 and/or the lower four-barlink 327 through the first coupling 329 coupled to the upper four-barlink 325 and yoke coupling 340 coupled to the first coupling 329. Inresponse to the shock pulse(s) traveling through the yoke coupling 340,the yoke coupling 340 may produce a downward pull (e.g., with respect tothe surface 659) of the second end of the linear actuator 337 and therod 338 coupled to the second end of the linear actuator 337 (e.g., viathe fourth fastener 347 b). The downward pull of the rod 338 may producea downward pull of the first end of the linear actuator 337 coupled tothe second portion of the rocker arm 335 (e.g., via the third fastener347 a). In response to the downward pull of the first end of the linearactuator 337 coupled to the second portion of the rocker arm 335, therocker arm 335 may swivel in an upward direction (e.g., pitch rotationalmotion in a clockwise direction) about the third fastener 347 a, whichmay produce a stretching of the rocker shaft 333 coupled to the firstportion of the rocker arm 335 (e.g., stretching between the firstfastener 345 a and the second fastener 345 b fixed to the respectiveportion of the chassis). The stretching of the rocker shaft 333 coupledbetween the first portion of the rocker arm 335 and the respectiveportion of the chassis may be resisted by a corresponding stretching ofthe spring 336 of the rocker shaft 333.

Additionally or alternatively, when the propulsion component 315contacts the dip 662, the shock pulse(s) may travel from the upperfour-bar link 325 and/or the lower four-bar link 327 through the firstcoupling 329 coupled to the upper four-bar link 325 and yoke coupling340 coupled to the first coupling 329. In response to the shock pulse(s)traveling through the yoke coupling 340, the yoke coupling 340 mayproduce an upward push (e.g., with respect to the surface 659) of thesecond end of the linear actuator 337 and the rod 338 coupled to thesecond end of the linear actuator 337 (e.g., via the fourth fastener 347b). The upward push of the rod 338 may produce an upward push of thefirst end of the linear actuator 337 coupled to the second portion ofthe rocker arm 335 (e.g., via the third fastener 347 a). In response tothe upward push of the first end of the linear actuator 337 coupled tothe second portion of the rocker arm 335, the rocker arm 335 may swivelin a downward direction (e.g., pitch rotational motion in acounterclockwise direction) about the third fastener 347 a, which mayproduce a compression of the rocker shaft 333 coupled to the firstportion of the rocker arm 335 (e.g., compression between the firstfastener 345 a and the second fastener 345 b fixed to the respectiveportion of the chassis). The compression of the rocker shaft 333 coupledbetween the first portion of the rocker arm 335 and the respectiveportion of the chassis may be resisted by a corresponding compression ofthe spring 336 of the rocker shaft 333. Thus, the shock absorbed by thepropulsion component 315 may be deflected (e.g., for smaller magnitudesof shock), or absorbed and dissipated (e.g., for greater magnitudes ofshock) by the spring 336 of the rocker shaft 333 (e.g., via a stretchingand/or compression of the spring 336). However, depending on the givenpropulsion component that contacts the bump or dip, the shocks may bedeflected unevenly throughout the rover chassis 603.

Accordingly, the rover suspension system may be controllable to operateaccording to the one or more active suspension modes to enable a moreeven deflection of shock throughout the rover chassis 603, and/or toenable maintaining the chassis 603 at a level orientation (e.g., withrespect to the lunar surface 659). In some embodiments, in the one ormore active suspension modes, the rover ECU selectively operates one ormore of the components of the suspension system 310. In someembodiments, while the rover 602 transports the respective payload 652and while employing active suspension, the linear actuator 337 may beselectively operated to adjust a relative orientation of a given controlleg 313 with respect to the lunar surface 659 when a propulsioncomponent 315 coupled to the given control leg 313 contacts or is aboutto contact (e.g., 1 s, 2 s, 5 s, 10 s, 15 s, etc. before contacting) abump or dip in the lunar surface 659. For example, as describedpreviously with reference to FIG. 3C, the first coupling 329 may includea link resolver 341 configured to measure an angle of rotation (e.g.,the second resolver angle, θ_(H)) of the first coupling 329 (and thusthe upper four-bar link 325 coupled to the first coupling 329) withrespect to the lunar surface 659. When a given propulsion componentcontacts unevenness in the lunar terrain 659, such as bump 661 or dip662, the angle of rotation measured by the link resolver 341 may changeas a result of a change in orientation of the control leg coupled to thegiven propulsion component. For example, in response to a givenpropulsion component contacting a dip 662 in the lunar surface 659, anelevation of the control leg coupled to the given propulsion componentmay decrease with respect to the lunar surface 659 (e.g., due to thelower elevation of the dip 662). In some embodiments, in response to agiven propulsion component contacting the dip 662 in the lunar surface659, a distance between the control leg (e.g., and the given propulsioncomponent coupled to the control leg) and the chassis 603 may increase.In response to a given propulsion component contacting a bump 661 in thelunar surface 659, an elevation of the control leg coupled to the givenpropulsion component may increase with respect to the lunar surface 659(e.g., due to the higher elevation of the bump 661). In someembodiments, in response to a given propulsion component contacting thebump 661 in the lunar surface 659, the distance between the control leg(e.g., and the given propulsion component coupled to the control leg)and the chassis 603 may decrease.

In some embodiments, in response to detecting a change in the angle ofrotation measured by the link resolver 341, the ECU rover mayselectively operate the linear actuator 337 of the given control leg toadjust an orientation of the control leg to the higher elevation of thebump 661 or the lower elevation of the dip 662. For example, as shown inFIG. 6B, the propulsion component 615 a contacts the bump 661, which, asdescribed above, causes the control leg 613 a coupled to the propulsioncomponent 615 a to increase in elevation with respect to the lunarsurface 659. In response to the increase in elevation of the control leg613 a (e.g., as detected by the link resolver of the suspension systemof the control leg 613 a), the rover ECU may operate the linear actuatorof the suspension system of the control leg 613 a to lower the elevationof the control leg 613 a with respect to the surface. As discussedpreviously with respect to FIGS. 5A-5H, the linear actuator may beoperated to increase the effective length of the linear actuator (e.g.,L2) to change the orientation of the control leg 613 a and raise thecontrol leg 613 a with respect to the surface 659, as shown.Additionally, in FIG. 6B, concurrently, the propulsion component 615 bcontacts the dip 662, which, as described above, causes the control leg613 b coupled to the propulsion component 615 b to decrease in elevationwith respect to the surface 659. In response to the decrease inelevation of the control leg 613 b (e.g., as detected by the linkresolver of the suspension system of the control leg 613 b), the roverECU may operate the linear actuator of the suspension system of thecontrol leg 613 b to lower the elevation of the control leg 613 b withrespect to the surface. As discussed previously with reference to FIGS.5A-5H, the linear actuator may be operated to decrease the effectivelength of the linear actuator (e.g., L2) to change the orientation ofthe control leg 613 b and lower the control leg 613 b with respect tothe surface 659, as shown.

Thus, as shown in FIG. 6B, the respective linear actuators of thecontrol leg 613 a and the control leg 613 b may be selectively operatedto autonomously adapt the orientations (e.g., elevations) of the controllegs 613 a and 613 b to unevenness in the terrain. In this way, thechassis 603 of the rover 602 may remain (substantially (e.g., within 2,5, 10, 15, 20, 25, or 30 degrees of being)) level (e.g., about 0 degreesas measured along a surface (e.g., the top surface) of the medial memberof the rover chassis 603 (e.g., corresponding to medial member 207 inFIGS. 2A-2B)) with respect to a reference (e.g., the surface 659, orgravity) and maintain a ground clearance between the bottom surface ofthe modular payload 652 and the unevenness in the surface (e.g., thebumps 661 and dips 662) to prevent and/or diminish impacts between themodular payload 652 and the surface 659. Thus, one advantage of thepassive and active suspension modes of the rover suspension systemduring a transportation of a respective modular payload is that therespective modular payload, including the contents of the respectivemodular payload, may be safeguarded from damage during transport.

In some embodiments, the rover suspension system may be configurable toautomatically switch between operating according to the passive and theactive suspension modes. For example, the one or more processors of therover 602 may cause the suspension system to switch between the modes inresponse to detecting a trigger. In some embodiments, the trigger may bea load-based trigger. For example, during transportation of the modularpayload 652 described above, the ECU of the rover 602 may activelymonitor the force of gravity under each propulsion component 615 (e.g.,using one or more angular encoders of the suspension systems of thecontrol legs 613. If a respective propulsion component (e.g., 615 a)bears a force (e.g., weight) that exceeds a force threshold (e.g., 45,50, 60, 70, 90, 100, 125, 150, etc. kg), the ECU of the rover 602 cancause the suspension systems of the control legs 613 to operateaccording to the active suspensions mode, such that the rover 602 raisesthe respective propulsion component (e.g., 615 a) and cause shift aportion of the weight of the modular payload 652 to the other propulsioncomponents. Similarly, in some embodiments, the trigger may be anorientation-based trigger. For example, if the chassis orientationexceeds desired orientation thresholds (e.g., exceeds a roll threshold(e.g., 5, 10, 15, 20, 25, 30, or 45 degrees) when transporting themodular payload 652 cross-slope, as determined with respect to gravity(e.g., by an inertial measurement sensor)), the ECU of the rover cancause the suspension systems of the control legs 613 to operateaccording to the active suspension mode, such that the uphill propulsioncomponents (e.g., 615 a) are raised from the surface 659 and thedownhill propulsion components (e.g., 615 b) are lowered toward thesurface 659. Thus, in some embodiments, the ECU of the rover 602 may beconfigured to monitor the chassis orientation and propulsion componentload distribution when determining whether to operate the suspensionsystems of the control legs of the rover 602 according to the passive oractive suspension modes, such that the chassis 603 of the rover 602 maybe maintained at or near a level orientation with respect to gravityand/or the weight borne by the propulsion components 615 are maintainedat or near a relatively even distribution (e.g., within 0.5, 1, 2, 4, 5,8, or 10 kg of each other).

Rover Functional Modules and Associated Processes

Attention is now directed towards examples of functional modules thatare configured to interface with a rover. When interfaced with therover, the functional modules may communicate with the rover ECU toperform one or more actions associated with the functional modules, asdescribed below.

FIGS. 7A-7E illustrate examples of functional modules 764-766 configuredto interface with a rover 702 according to some embodiments of thedisclosure. In some embodiments, the rover 702 optionally corresponds torover 602, 502, and/or 202 shown in FIGS. 6A-6B, FIGS. 5A-5H, and/orFIGS. 2A-2B, respectively. As described herein, the rover may beconfigured to retrieve, transport, and/or deposit payloads on a surface(e.g., a lunar surface). In some embodiments, the rover may beconfigurable to perform one or more additional actions and/or functionsby interfacing the rover with a respective functional module, asdescribed below.

FIGS. 7A-7B illustrate examples of a vehicle functional module 764 and asurface science functional module 766, respectively. As shown in FIG.7A, in some embodiments, the vehicle functional module 764 may comprisea crew stand 763 and an interface structure, including one or moreinterface receptacles (e.g., pins) 765 and one or more guides 786. Insome embodiments, the one or more interface receptacles 765 and/or theone or more guides 786 may be configured to physically andcommunicatively link the vehicle functional module 764 (and itscomponents) to the rover (and its components). While shown along a frontportion of the vehicle functional module 764, the one or more interfacereceptacles 765 and/or the one or more guides 786 may be alternativelyor additionally provided along one or more side portions of the vehiclefunctional module 764, or bottom portions of the vehicle functionalmodule 764. In some embodiments, the crew stand 763 may support one ormore users (e.g., astronauts) 771. As shown in FIG. 7A, the vehiclefunctional module 764 may include a control panel 770 disposed on thecrew stand 763. In some embodiments, the control panel 770 may beoperable by the one or more users 771 to manually control one or morefunctions of the rover, as discussed in more detail below.

As shown in FIG. 7B, in some embodiments, the surface science functionalmodule 766 may comprise a remote science mast 767 and a robotic arm 768.In FIG. 7B, the remote science mast 767 and the robotic arm 768 areshown in a collapsed state. In some embodiments, once the surfacescience functional module 766 is interfaced with the rover, the remotescience mast 767 and/or the robotic arm 768 may be deployed for use. Insome embodiments, the surface science functional module 766 may includean interface structure (not shown) configured to physically andcommunicatively link the surface science module 766 (and its components)to the rover (and its components). For example, the interface structure(not shown) may be similar to the interface structure (e.g., interfacereceptacle 765 and/or guides 786) of the vehicle functional module 764shown in FIG. 7A.

FIGS. 7C-7D illustrate examples of the vehicle functional module 764 andthe surface science functional module 766, respectively, interfaced withthe rover 702. As shown in FIG. 7C, in some embodiments, the vehiclefunctional module 764 may be interfaced with the rover 702 to configurethe rover 702 as a rover vehicle. For example, with the vehiclefunctional module 764 linked to the medial member 707 of the chassis 703of the rover 702, the rover 702 is configured to be manually driven as arover vehicle by the one or more users 771. The one or more users 771may use the control panel 770 to drive (e.g., accelerate, steer, brake,etc.) the rover 702 on the planetary surface. For example, the controlpanel 770 may be electrically coupled to the rover ECU (e.g.,corresponding to ECU 104 in FIGS. 1A-1B), allowing the systems of therover (e.g., motor assembly, suspension system, latching system, etc.)to be operated according to instructions received from the control panel770 (e.g., according to user input received at the control panel 770).As shown in FIG. 7C, the rover 702 may transport a modular payload 752(e.g., carrying crew tools, instruments, scientific samples, etc.) asthe rover 702 is manually driven by the one or more users 771. In someembodiments, the plurality of latches/hooks of the latching system ofthe rover 702 (e.g., corresponding to the plurality of latches/hooks 553in FIGS. 5F-5H) and/or the plurality of latch receptacles of the modularpayload 752 (e.g., corresponding to the plurality of latch receptacles554 in FIGS. 5F-5H) may be disposed in the rover 702 and the modularpayload 752, respectively, in such a way so as to provide sufficientclearance for the chassis 703 to retrieve the modular payload 752. Insome embodiments, when the vehicle functional module 764 is attached tothe rover chassis 703, the modular payload 752 may be retrieved (e.g.,via the rover latching system) alternatively so as to accommodate thevehicle functional module 764. For example, the modular payload 752 maybe positioned below and retrieved toward a front end of the rover 702when the functional module 764 is attached to the rover chassis 703, andthe modular payload 752 may be positioned below and retrieved moretoward a center of the rover 702 when the functional module 764 is notinterfaced with the rover chassis 703.

It should be understood that the rover 702, while configured to functionas a rover vehicle, may be configured to perform any of the operationsdescribed with reference to FIGS. 5A-6B, such as, for example, payloadretrieval, adaptive suspension, etc. For example, the chassis 703 of therover 702 may be lowered with respect to the reference to allow for easeof user ingress and egress on the crew stand 763. A second crew stand763 may be interfaced to the front of the rover 702 (e.g., in place ofthe modular payload 752) to enable additional users (e.g., crew members)to ride on the rover 702.

As shown in FIG. 7D, in some embodiments, the surface science functionalmodule 766 may be interfaced with the rover 702 to configure the rover702 as a science mobility system. In some embodiments, the surfacescience functional module 766 may be interfaced with the medial member707 of the rover chassis. For example, with the surface sciencefunctional module 766 linked to the medial member 707 of the chassis ofthe rover 702, the rover 702 is configured to (e.g., autonomously or viaexternal control) perform scientific mission objectives. As shown, theremote science mast 767, the robotic arm 768 and the solar panel array711 may be deployed for use in conducting surface science datacollection, such as collecting soil/dust samples (e.g., stored withincompartment 769), collecting rocks, performing surface scans, and thelike. For example, the remote science mast 767 and the robotic arm 768may be electrically coupled to the rover ECU (e.g., corresponding to ECU104 in FIGS. 1A-1B), allowing the systems of the rover (e.g., motorassembly, suspension system, latching system, etc.) to be operated withthe remote science mast 767 and the robotic arm 768. As shown in FIG.7D, the rover 702 may transport a modular payload 752 as the rover 702conducts surface science data collection (e.g., for storing thecollected samples). In some embodiments, the surface science functionalmodule 766 may not extend below (e.g., vertically) the bottom surface ofthe medial member 707 (e.g., to prevent the surface science functionalmodule 766 and its components from interfering with payload retrievalwhile the surface science functional module 766 is interfaced with therover chassis).

FIG. 7E illustrates an example top-deck interface structure of the rover702 for interfacing a functional module to the chassis 703 of the rover702. As described above, functional modules may be physically andcommunicatively linked to the chassis 703 to allow the functionalmodules to communicate with the rover ECU to perform one or more actionsassociated with the functional modules. For example, a respectivefunctional module (e.g., the vehicle functional module 764 and/or thesurface science functional module 766) may be linked to the rover ECUvia the medial member 707. In some embodiments, the respectivefunctional module may additionally or alternatively be linked to therover ECU via a top-deck interface structure, as described below.

As shown in FIG. 7E, the top-deck interface structure may comprise aconical latch 784 and a top hook 783 disposed on a top surface of thechassis 703. For example, the conical latch 784 and the top hook 783 maybe disposed at or near an edge of a flank of the chassis 703. As shownin the detailed view 731 (e.g., a planar view of an interior portion ofthe first side 705 of the rover chassis 703), the first side 705 of thechassis 703 may include a first conical latch 784 a and a first top hook783 a disposed on the top surface of the first side 705. In someembodiments, the first top hook 783 a may be configured to selectivelyprotrude upward from the top surface of the first side 705. In someembodiments, the respective functional module (e.g., such as the vehiclefunctional module 764 or the surface science functional module 766) maybe placed atop two or more of the conical latches 784 and the top hooks783 at either end of the chassis 703 to link the respective functionalmodule to the rover ECU, rather than interfaced directly to the medialmember 707 as shown in FIGS. 7C-7D. For example, the respectivefunctional module may comprise one or more corresponding conicalrecesses (e.g., similar or corresponding to the guides 786 in FIG. 7A)and hook receptacles (e.g., similar or corresponding to thereceptacles/pins 765 in FIG. 7A) configured to receive/interface withthe conical latches 784 and the top hooks 783, respectively. Forexample, the one or more corresponding conical recesses and hookreceptacles may be provided in a bottom/interior portion of therespective functional module that rests atop the edges of the flanks ofthe chassis 703. In some embodiments, the top hooks 783 may becontrollable by the rover ECU to protrude upward to engage with the hookreceptacles of the respective functional module when the respectivefunctional module is placed atop the conical latches 784, such that therespective functional module is secured to the chassis 703.

In some examples, with the respective functional module secured to thechassis 703 (e.g., as similarly shown in FIGS. 7C-7D), the chassis 703may support a weight of the respective functional module. For example,referring to FIG. 7C, when the vehicle functional module 764 is attachedto a rear end of the rover 702, the top portions of the chassis 703 atthe rear end of the rover 702 optionally exert an upward force on thebottom portion of the vehicle functional module 764, thereby supportingthe weight of the vehicle functional module 764 while the vehiclefunctional module 764 is attached to the rover 702 and/or while therover 702 is in motion (e.g., or performing some other action).Similarly, with reference to FIG. 7D, when the surface sciencefunctional module 766 is attached to a front end of the rover 702, thetop portions of the chassis 703 at the front end of the rover 702optionally exert an upward force on the bottom portion of the surfacescience functional module 766, thereby supporting the weight of thesurface science module 766 while the surface science functional module766 is attached to the rover 702 and/or while the rover 702 is in motion(e.g., or performing some other action).

It should be understood that, although not explicitly described herein,the rover 702 may be configured to perform various autonomous and manualoperations as the rover 702 functions as a rover vehicle and/or as ascience mobility system. Additionally or alternatively, additional typesof functional modules may be interfaced with the rover 702 to adapt theoperations of the systems of the rover 702 to perform one or morespecific actions. For example, a drilling functional module may beinterfaced with the rover 702 to perform drilling actions on theplanetary surface, or a crew rescue functional module may be interfacedwith the rover 702 (e.g., containing a stretcher/gurney) fortransporting an injured person, and the like.

Multi-Rover Retrieval, Transportation, and/or Deposition of LargePayloads

Attention is now directed towards example coordinated operations of aplurality of rovers in retrieving a respective payload for thesubsequent transportation and/or deposition of the respective payload.The respective payload may be located at a respective location on aplanetary surface (e.g., the surface of a moon) which, for ease ofillustration and explanation, is an even (e.g., substantially flat)location on the planetary surface. The respective payload may be a largepayload (e.g., a payload having a size exceeding the retrieval andtransportation capabilities of a single rover). As described below, asystem including a plurality of rovers may be provided for performingjoint actions involving large payloads, where the various operations ofeach individual rover of the system may be (e.g., at least substantiallyand/or autonomously) controlled by the rover ECU.

FIGS. 8A-8D illustrate an example retrieval and transportation of alarge payload 882 using a multi-rover system according to someembodiments of the disclosure. In some embodiments, the multi-roversystem optionally corresponds to system 150 shown previously in FIG. 1B.As shown in FIG. 8A, the multi-rover system may include a first rover802 a and a second rover 802 b. In some embodiments, the first rover 802a and the second rover 802 b optionally each correspond to the rover202/502/602 shown previously in FIGS. 2A-2B, 5A-5H, and 6A-6B,respectively. As discussed previously with reference to FIG. 1B, therespective ECUs of the first rover 802 a and the second rover 802 b maybe configured to communicate via their respective communications units(e.g., communication units 116 a and 116 b). For example, as discussedbelow, the ECU of the first rover 802 a may be configured to communicatewith the ECU of the second rover 802 b via a communications link betweentheir respective communications units to perform joint actions involvingthe large payload 882.

As shown in FIG. 8A, the large payload 882 may have a size (e.g., aheight, width, and/or length) that may exceed the retrieval and/ortransportation capabilities of a single rover. In some embodiments, arespective payload may additionally or alternatively have anorientation, a shape, and/or a vulnerability (e.g., a sensitivity orfragility) that may exceed the retrieval and/or transportationcapabilities of a single rover. Accordingly, a plurality of rovers maybe provided for performing coordinated retrieval, transportation, and/ordeposition of the respective payload. As shown in FIG. 8A, for example,the large payload 882 may be a large pipe having a smooth andcylindrical surface 881 and a plurality of circular projections 883disposed along the surface 881.

In some embodiments, the first rover 802 a and the second rover 802 bmay, via their respective one or more sensors 820 a and 820 b,respectively, detect and identify a location of the payload 882 on thesurface on which the rovers are operating. As shown in FIG. 8A, afteridentifying the location of the payload 882, the first rover 802 a andthe second rover 802 b may be operated (e.g., via their respective roverECUs) to (e.g., autonomously and concurrently) approach the payload 882.For example, the respective rover ECUs may concurrently drive a firstplurality of propulsion components 815 a (e.g., using the motor assembly(e.g., corresponding to motor assembly 322 in FIG. 3A) associated witheach propulsion component) of the first rover and a second plurality ofpropulsion components 815 b (e.g., using the motor assembly (e.g.,corresponding to motor assembly 322 in FIG. 3A) associated with eachpropulsion component) of the second rover to drive the first rover 802 aand the second rover 802 b toward the payload 882. In some embodiments,the first rover 802 a optionally communicates with the second rover 802b using their respective antennas 812 a and 812 b (e.g., incommunication with their respective communications units).

In some embodiments, as the first rover 802 a and the second rover 802 bare driven toward the payload 882, the respective rover ECUs may utilizedata (e.g., image data) captured via the respective one or more sensors820 a and 820 b to position the respective interiors of each chassisabove and/around respective portions of the payload 882. For example,first captured data may be utilized by the ECU of the first rover 802 ato position the interior 801 a of the chassis 803 a of the first rover802 a above and/or around a first portion of the payload 882 (e.g., afirst end of the payload 882), and second captured data may be utilizedby the ECU of the second rover 802 b to position the interior 801 b ofthe chassis 803 b of the second rover 802 b above and/or around a secondportion of the payload 882 (e.g., a second end of the payload 882).Particularly, as discussed below, the first rover 802 a and the secondrover 802 b may concurrently position themselves above the first portionof the payload 882 and the second portion of the payload 882,respectively, to retrieve the payload 882.

In some embodiments, when the first rover 802 a and the second rover 802b are each positioned above the payload 882, the first plurality ofpropulsion components 815 a of the first rover 802 a and the secondplurality of propulsion components 815 b of the second rover 802 boptionally cease to be driven, such that the first rover 802 a and thesecond rover 802 b remain stationary above the payload 882. In someembodiments, the first rover 802 a and the second rover 802 b may ceasedriving forward when the first rover 802 a and the second rover 802 bdetect that respective portions (e.g., a threshold amount of a topsurface of each of the first end and the second end of the payload 882,respectively) of the payload 882 are positioned below the first rover802 a and the second rover 802 b. In some embodiments, the first rover802 a and the second rover 802 b each comprises a suspension system(e.g., corresponding to suspension system 310 in FIGS. 3A-3B) disposedwithin their respective chassis 803 a and 803 b. In some embodiments,the suspension system of the first rover 802 a and the suspension systemof the second rover 802 b each comprises the same or similar componentsand/or characteristics as the rover suspension system 310 describedpreviously with reference to FIGS. 3A-3C. As discussed above withreference to FIGS. 3A-3C, the suspension system of the first rover 802 amay form a part of each control leg 813 a of the first rover 802 a andthe suspension system of the second rover 802 b may form a part of eachcontrol leg 813 b of the second rover 802 b. In some embodiments, whenthe first rover 802 a is positioned above a first portion of the payload882 and the second rover 802 b is positioned above a second portion ofthe payload 882, the suspension system of each control leg 813 a of thefirst rover 802 a and the suspension system of each control leg 813 b ofthe second rover 802 b may be selectively operated (e.g., by theirrespective ECUs) to initiate the process of retrieving the payload 882.Particularly, the suspension system of the first rover 802 a and thesuspension system of the second rover 802 b may be operated (e.g.,according to the methods described previously with reference to FIGS.5B-5E) to selectively lower the chassis 803 a of the first rover 802 aand the chassis 803 b of the second rover 802 b with respect to areference (e.g., the surface 859 on which the first rover 802 a and thesecond rover 802 b are placed, or a point or plane on/along a bottomsurface of the chassis 803 a and 803 b of the first rover 802 a and thesecond rover 802 b, respectively) and toward the top surface 881 of thepayload 882, as discussed below.

In some embodiments, the first rover 802 a may communicate with thesecond rover 802 b via their respective antennas 812 a and 812 b toinitiate coordinated retrieval of the payload 882. As similarlydescribed with reference to FIGS. 5A-5H, the chassis 803 a of the firstrover 802 a and the chassis 803 b of the second rover 802 b areselectively lowered with respect to the reference (e.g., the surface 859on which the first rover 802 a and the second rover 802 b are placed)and thus oriented closer toward the top surface of the first portion(e.g., the first end) and the second portion (e.g., the second end) ofthe payload 882, respectively. The lowering of the chassis 803 a of thefirst rover and the lowering of the chassis 803 b of the second rover802 b may occur concurrently (e.g., initiated at substantially the sameinstance in time as coordinated by the ECU of the first rover 802 a andthe ECU of the second rover 802 b). For example, after the ECU of thesecond rover 802 b has determined that the chassis 803 b of the secondrover 802 b is positioned above the second portion of the payload 882,the ECU of the second rover 802 b may send one or more signals to theECU of the first rover 802 a conveying that the second rover 802 b ispositioned above the second portion of the payload 882. Once the ECU ofthe first rover has determined that the chassis 803 a of the first rover802 a is positioned above the first portion of the payload 882, andafter receiving the one or more signals from the ECU of the second rover802 b, the ECU of the first rover 802 a may communicate one or morecommands to the ECU of the second rover 802 b (e.g., via theirrespective communications antennas 812 a and 812 b) to trigger the ECUof the second rover 802 b to initiate lowering of the chassis 803 b ofthe second rover 802 b when the ECU of the first rover 802 aconcurrently initiates lowering of the chassis 803 a of the first rover802 a. As described in detail with respect to FIGS. 5B-5E, respectiveorientations of the first plurality of control legs 813 a of the firstrover 802 a and respective orientations of the second plurality ofcontrol legs 813 b of the second rover 802 b may be changed (e.g., inresponse to operation of their respective suspension systems) to causethe chassis 803 a of the first rover 802 a and the chassis 803 b of thesecond rover 802 b to be selectively lowered toward the top surface ofthe first portion of the payload 882 and the second portion of thepayload 882, respectively.

In some embodiments, the suspension system of the first rover 802 a andthe suspension system of the second rover 802 b may be operated (e.g.,by their respective rover ECUs) to lower the chassis 803 a of the firstrover 802 a and the chassis 803 b of the second rover 802 b until the(e.g., bottom surface of the medial member of the) chassis 803 a of thefirst rover 802 a and the chassis 803 b of the second rover 802 b arelowered close enough to the top surface of the first portion and of thesecond portion of the payload 882 to retrieve the payload 882. Forexample, the ECU of the first rover 802 a and the ECU of the secondrover 802 b may each be configured to determine a respective angle of aportion of each chassis 803 a and 803 b, respectively, with respect tothe reference (e.g., the surface 859, or the top surface of the payload882). In some embodiments, the respective angle of the portion of eachchassis 803 a and 803 b optionally corresponds to a distance between(e.g., a bottom surface of the medial member of) each chassis 803 a and803 b and the top surface of the first portion of the payload 882 andthe second portion of the payload 882. In some embodiments, when thecomputed respective angle corresponds to a relative threshold angle(e.g., relative to the size of the payload, where the threshold angle is30 degrees, 35 degrees, 45 degrees, 50 degrees, 60 degrees, 65 degrees,70 degrees, etc.) with respect to the reference (e.g., the surface 859,or the top surface 881 of the payload 882), the ECU of the first rover802 a and the ECU of the second rover 802 b may operate the suspensionsystem of the first rover 802 a and the suspension system of the secondrover 802 b to cease lowering the chassis 803 a of the first rover 802 band the chassis 803 b of the second rover 802 b, respectively.

In some embodiments, different sized payloads (or portions of thepayloads) will have different associated angles at which the first rover802 a and/or the second rover 802 b may stop lowering to retrieve thepayloads. For example, a taller payload (e.g., a payload having agreater height dimension than that shown in FIGS. 8A-5D, or a payloadhaving taller portions with which each rover may interlock) may requirethe first rover 802 a and/or the second rover 802 b to stop lowering ata first relative threshold angle that is smaller than a second relativethreshold angle that may be required for retrieving a shorter modularpayload (e.g., a payload having a smaller height dimension than thatshown in FIGS. 8A-5D, or a payload having shorter portions at which eachrover may interlock with). In some such embodiments, the first rover 802a may communicate with the second rover 802 b (e.g., via theirrespective antennas 812 a and 812 b associated with their respectivecommunications unit) to determine an instance in time at which eachrover has lowered their respective chassis 803 a/803 b to meet therelative threshold angle with respect to a respective portion of thepayload 882 that is beneath the interior portion of the chassis 803a/803 b. For example, as shown in FIG. 8B, the first rover 802 a may belowered a first amount according to the above methods to position thechassis 803 a to meet the relative threshold angle with respect to thetop surface of the first portion (e.g., the first end) of the payload882 and the second rover 802 b may be lowered a second amount accordingto the above methods to position the chassis 803 b to meet the relativethreshold angle with respect to the top surface of the second portion(e.g., the second end) of the payload 882. In some embodiments (e.g., inwhich the payload 882 has a consistent height/diameter throughout a bodyof the payload 882 and/or the surface 859 on which the payload 882 isplaced is flat/even), the first rover 802 a may be lowered the sameamount as the second rover 802 b is lowered. In some embodiments (e.g.,in which the first end/portion of the payload 882 has a height/diameterthat is different from that of the second end/portion of the payload 882and/or the surface 859 on which the payload 882 is placed is uneven),the first rover 802 a may be lowered a different amount than an amountthat the second rover 802 b is lowered.

In some embodiments, when the chassis 803 a of the first rover 802 a andthe chassis 803 b of the second rover 802 b have been lowered withrespect to the reference (e.g., the surface 859 or the top surface ofthe first portion and of the second portion of the payload 882) to arespective elevation above the top surface 881 of the payload 882 (e.g.,abutting the top surface of the payload 882 or within 2 cm, 5 cm, 7 cm,10 cm, 15 cm, etc. above the top surface of the payload 882) to at leastpartially surround the first portion and the second portion of thepayload 882, as shown in FIG. 8B, the ECU of the first rover 802 a maycommunicate with the ECU of the second rover 802 b (e.g., via antennas812 a and 812 b) to initiate one or more latching operations forretrieval of the payload 882. In some embodiments, once the ECU of thesecond rover 802 b has determined that the chassis 803 b of the secondrover 802 b has been lowered to at least partially surround the secondportion of the payload 882, the ECU of the second rover 802 b may sendone or more signals to the ECU of the first rover 802 a to convey thatthe chassis 803 b of the second rover 802 b is at the respectiveelevation above the top surface 881 of the second portion of the payload882. Once the ECU of the first rover 802 a has determined that thechassis 803 a of the first rover 802 a has been lowered to at leastpartially surround the first portion of the payload 882, and afterreceiving the one or more signals from the ECU of the second rover 802b, the ECU of the first rover 802 a may communicate one or more commandsto the ECU of the second rover 802 b (e.g., via their respectivecommunications antennas 812 a and 812 b) to trigger the ECU of thesecond rover 802 b to initiate attaching of the chassis 803 b of thesecond rover 802 b to the second portion of the payload 882 when the ECUof the first rover 802 a concurrently initiates attaching of the chassis803 a of the first rover 802 a to the first portion of the payload 882.As described above with reference to FIGS. 5F-5H, the first rover 802 aand the second rover 802 b may each comprise a latch system configuredto latch with a respective portion of the payload 882. In someembodiments, the rover latch system optionally corresponds to the latchsystem 206/506 shown in FIGS. 2B and 5F-5H, respectively.

As described previously with respect to FIG. 5F, the latch system (e.g.,latch system 506) of the first rover 802 a and the latch system of thesecond rover 802 b may each be disposed within the chassis 803 a of thefirst rover 802 a and the chassis 803 b of the second rover 802 b,respectively. In some embodiments, the rover latch system of the firstrover 802 a and the rover latch system of the second rover 802 b eachcomprise the same or similar components and/or characteristics as therover latch system 506 described previously with reference to FIGS.5F-5H. For example, the latch system of each of the first rover 802 aand the second rover 802 b may comprise a plurality of hooks/appendages(e.g., 553) that may be configured to protrude outwardly from withininterior sides of the chassis 803 a/803 b to engage with and/or grip arespective portion of payload 882. In some embodiments, the plurality ofhooks of each latch system may be configured to accommodate variouspossible shapes, surface textures, and/or surfaces of the payload 882.For example, the plurality of hooks of each latch system may comprise orbe coated/lined with a friction material (e.g., a rubber-like material)to enable the plurality of hooks to grip the respective portion of thepayload (e.g., such as surface 881), and/or the plurality of hooks maybe provided with a shape (e.g., an L-shape) and/or a length that enablesthe plurality of hooks to engage with a bottom portion/surface of therespective portion of the payload. The first rover 802 a and the secondrover 802 b may thus be configured to together retrieve any payload solong as the payload fits within the interior of each of their respectiverover chassis 803 a/803 b. As described above with reference to FIG. 5F,the plurality of hooks of each latch system may be controllable via oneor more motors (e.g., 555) that cause the plurality of hooks of eachlatch system to protrude from the interior portions of the chassis 803 aof the first rover 802 a and the chassis 803 b of the second rover 802 b(e.g., according to the methods described previously in FIGS. 5F-5H).

In some embodiments, the one or more motors of the latch system of thefirst rover 802 a and of the second rover 802 b may each be controllableto selectively cause the plurality of hooks to engage with the firstportion (e.g., the first end) and the second portion (e.g., the secondend) of the payload 882, respectively. For example, in FIG. 8B, the ECUof the first rover 802 a may cause the plurality of hooks of the latchsystem of the first rover 802 a to engage with and/or grip the first endof the payload 882. Concurrently, the ECU of the second rover 802 a maycause the plurality of hooks of the latch system of the second rover 802b to engage with and/or grip the second end of the payload 882. Forexample, as mentioned above with respect to FIG. 8A, the payload 882 maycomprise the surface 881 and the circular projections 883. As shown inFIG. 8B, the circular protrusions 883 may create a spacing between thesurface 881 and the surface 859 on which the payload 882 is placed. Theplurality of hooks of the latch system of each of the first rover 802 aand the second rover 802 b may thus grip a bottom portion of the surface881 that is between a bottom portion of the circular protrusions 883 andthe surface 859. The plurality of hooks of the latch system of the firstrover 802 a and the plurality of hooks of the latch system of the secondrover 802 b may thus securely retrieve the first portion and the secondportion of the payload 882, respectively.

Thus, as outlined above, the system comprising the first rover 802 a andthe second rover 802 b may be autonomously operated to locate, approach,and retrieve a large payload for subsequent transportation and/ordeposition of the large payload at a respective location on the surface859 (e.g., the lunar surface). As discussed above, the retrieval of thelarge payload according to the above example processes provides for aninput-free, effective, and long-lasting mobility platform which maygreatly reduce time and resources spent manually loading, transporting,and unloading large payloads. Further, as an advantage, efforts andresources may be focused and allocated toward more significant and/orspecialized lunar mission objectives in which human input may berequired, such as exploration, testing, construction and the like.

In some embodiments, following the retrieval of the payload 882, the ECUof the first rover 802 a may communicate with the ECU of the secondrover 802 b to initiate processes for transporting and/or depositing thepayload 882. In some embodiments, once the ECU of the second rover 802 bhas determined that the plurality of latches of the second rover 802 bhave been caused to engage with the second portion (e.g., the secondend) of the payload 882, the ECU of the second rover 802 b may send oneor more signals to the ECU of the first rover 802 a to convey that thechassis 803 b of the second rover 802 b is attached to the sectionportion of the payload 882. Once the ECU of the first rover 802 a hasdetermined that the plurality of latches of the first rover 802 a havebeen caused to engage with the first portion (e.g., the first end) ofthe payload 882, and after receiving the one or more signals from theECU of the second rover 802 b, the ECU of the first rover 802 a maycommunicate one or more commands to the ECU of the second rover 802 b(e.g., via their respective communications antennas 812 a and 812 b) totrigger the ECU of the second rover 802 b to initiate raising of thechassis 803 b of the second rover 802 b when the ECU of the first rover802 a concurrently initiates raising of the chassis 803 a of the firstrover 802 a. For example, the suspensions system of the first rover 802a and the suspension system of the second rover 802 b may beconcurrently operated to change respective orientations of the firstplurality of control legs 813 a of the first rover 802 a and respectiveorientations of the second plurality of control legs 813 b of the secondrover 802 b, respectively, to gradually raise the chassis 803 a of thefirst rover 802 a and the chassis 803 b of the second chassis 803 b in acoordinated manner. In some embodiments, the chassis 803 a of the firstrover 802 a and the chassis 803 b of the second rover 802 b may begradually raised at a same rate to maintain the payload 882 within alevel (e.g., flat) orientation with respect to the surface 859 as thechassis 803 a of the first rover 802 a and the chassis 803 b of thesecond rover 802 b are raised. Raising the first portion of the payload882 at a different rate from the second portion of the payload 882 couldotherwise cause the first portion of the payload 882 and/or the secondportion of the payload 882 to become unattached from the plurality ofhooks of the chassis 803 a of the first rover 802 a and/or the pluralityof hooks of the chassis 803 b of the second rover 802 b, respectively.The suspension system of the first rover 802 a and the suspension systemof the second rover 802 b may each be operated to raise their respectivechassis 803 a/803 b and the payload 882 attached thereto according toany of the methods described previously with respect to FIGS. 5A-5H. Thechassis 803 a of the first rover 802 a and the chassis 803 b of thesecond rover 802 b may be raised to an upright position to maintain aground clearance for a bottom surface of the payload 882 duringtransportation.

In some embodiments, as mentioned above, the first end/portion of thepayload 882 may have a height/diameter that is different from that ofthe second end/portion of the payload 882. Additionally oralternatively, in some embodiment, the surface 859 on which the payload882 is placed may be uneven (e.g., may contain bumps and/or dips), whichmay cause the first portion and/or the second portion of the payload 882to be oriented on the surface 859 at different heights. In some suchembodiments, the first rover 802 a may be raised a different amount thanan amount that the second rover 802 b is raised. For example, in aninstance in which the first portion of the payload 882 has a diameterthat is greater than that of the second portion of the payload 882, theECU of the first rover 802 a may cause the chassis 803 a of the firstrover 802 a to be raised a first amount, and the ECU of the second rover802 b may cause the chassis 803 b of the second rover 802 b to be raiseda second amount, greater than the first amount. As another example, inan instance in which the second portion of the payload 882 is placed onan elevated surface of the surface 859 (e.g., such as a bump in thesurface 859), such that the second portion of the payload 882 is at aheight that is greater than that of the first portion of the payload882, the ECU of the first rover 802 a may cause the chassis 803 a of thefirst rover 802 a to be raised a first amount, and the ECU of the secondrover 802 b may cause the chassis 803 b of the second rover 802 b to beraised a second amount, less than the first amount. Additionally, insome embodiments, the chassis 803 a of the first rover 802 a may beraised at a different rate than the chassis 803 b of the second rover802 b to account for differences in payload height and/or orientation.

In some embodiments, once the chassis 803 a of the first rover 802 a andthe chassis 803 b of the second rover 802 b are in the raised position,as shown in FIG. 8C, motor assembly of the first rover 802 a and themotor assembly of the second rover 802 b may be operated by theirrespective rover ECUs to drive the plurality of propulsion components815 a of the first rover 802 a and the plurality of propulsioncomponents 815 b of the second rover 802 b. For example, the first rover802 a may communicate with the second rover 802 b (e.g., via theirrespective antennas 812 a and 812 b) to initiate transportation of thepayload 882 to a respective location on the surface 859. In someembodiments, the motor assembly of the first rover 802 a (e.g.,particularly, the steering actuator coupled to each propulsioncomponent) may be operated to cause the propulsion components 815 a ofthe first rover 802 a to face (e.g., to be steered in) a respectivedirection corresponding to the respective location. Similarly, the motorassembly of the second rover 802 b (e.g., particularly, the steeringactuator coupled to each propulsion component) may be operated to causethe propulsion components 815 b of the second rover 802 b to face (e.g.,to be steered in) the respective direction corresponding to therespective location. In some embodiments, the motor assembly of thefirst rover 802 a (e.g., particularly, the wheel actuator coupled toeach propulsion component) may be operated to cause the propulsioncomponents 815 a of the first rover 802 a to be driven (e.g., to rotate)in the respective direction toward the respective location.Concurrently, the motor assembly of the second rover 802 b (e.g.,particularly, the wheel actuator coupled to each propulsion component)may be operated to cause the propulsion components 815 b of the secondrover 802 b to be driven (e.g., to rotate) in the respective directiontoward the respective location.

In some embodiments, the propulsion components 815 a of the first rover802 a and the propulsion components 815 b of the second rover 802 b mayeach be driven (e.g., by their respective motor assemblies) at a samespeed (e.g., 1 m/s, 2 m/s, 2.5 m/s, 3.5 m/s, 5 m/s, 8 m/s, 10 m/s, etc.)and/or at zero (e.g., or constant) acceleration to smoothly and securelytransport the payload 882 to the respective location. For example, asthe first rover 802 a travels at a respective speed, the first portion(e.g., the first end) of the payload 882 attached to the chassis 803 aof the first rover 802 a may also travel (e.g., be transported by thefirst rover 802 a) toward the respective location at the respectivespeed. Likewise, as the second rover 802 b travels at the respectivespeed, the second portion (e.g., the second end) of the payload 882attached to the chassis 803 b of the second rover 802 b may also travel(e.g., be transported by the second rover 802 b) toward the respectivelocation at the respective speed. The payload 882 may thus betransported to the respective location at the respective speed asdetermined by the relative speeds of motion of the first portion and thesecond portion of the payload 882, which may also allow the payload 882to remain within one or more orientations (e.g., remain substantiallylevel) with respect to the surface 859 during transport. The ECU of thefirst rover 802 a may remain in constant communication with the ECU ofthe second rover 802 b to maintain the speeds of the first rover 802 aand the second rover 802 b at the respective speed, and thus to preventthe first portion of the payload 882 and/or the second portion of thepayload 882 from becoming unattached from the chassis 803 a of the firstrover 802 a and/or the chassis 803 b of the second rover 802 b.

In some embodiments, the first rover 802 a and the second rover 802 bmay be configured to adjust their relative orientations with respect tothe other, to change a spatial orientation of the payload 882 during thecoordinated transportation of the payload 882. For example, the firstrover 802 a and the second rover 802 b may be reoriented with respect tothe other to transport the payload 882 in a horizontal orientation(e.g., rather than a vertical orientation, as shown in FIG. 8C), suchthat an axis that extends through the payload 882 is substantiallyperpendicular to an axis parallel to the direction of travel of thefirst rover 802 a and the second rover 802 b. The ECU of the first rovermay operate the motor assembly coupled to each of the propulsioncomponents 815 a of the first rover 802 a to cause the first rover 802 ato travel at a reduced speed (e.g., and/or to come to a stop). The ECUof the second rover 802 b may operate the motor assembly coupled to eachof the propulsion components 815 b to steer each of the propulsioncomponents 815 b and/or to cause the second rover 802 b to travel at anincreased speed (e.g., faster than a speed of the first rover 802 a). Asan illustrative example, from a top view (e.g., of that shown in FIG.8C), the payload 882 may be rotated in a clockwise direction if thepropulsion components 815 b are steered toward the left as the secondrover 802 b travels in the respective direction, or the payload 882 maybe rotated in a counter clockwise direction if the propulsion components815 b are steered toward the right as the second rover 802 b travels inthe respective direction. The ECU of the second rover 802 b may thencommunicate with the ECU of the first rover 802 a to trigger the ECU ofthe first rover 802 a to operate the propulsion components 815 a of thefirst rover 802 a to jointly transport the payload 882 in a horizontalorientation.

As discussed below, during the coordinated transportation of the payload882, the first rover 802 a and/or the second rover 802 b may encounterone or more occurrences of unevenness on the surface 859. In someembodiments, the suspension system of the first rover 802 a and/or thesuspension system of the second rover 802 b may be configured to adaptto such occurrences of unevenness during transport, such that thechassis 803 a of the first rover 802 a and the chassis 803 b of thesecond rover and/or the payload 882 may remain substantially level withrespect to the (e.g., lunar) surface 859.

As shown in FIG. 8D, the first rover 802 a and the second rover 802 bmay be transporting the payload 882 over the surface 859 toward therespective location. As mentioned above, the surface may includeunevenness (e.g., obstacles or hindrances to travel, such as rocks,dips, craters, etc.). For extreme instances of unevenness, such as deepcraters, the ECU of the first rover 802 a and the ECU of the secondrover 802 b may be configured to detect a respective crater using theirrespective one or more sensors 820 a and 820 b. In such instances, theECU of the first rover 802 a may communicate with the ECU of the secondrover 802 b to initiate coordinated operation of the plurality ofpropulsion components 815 a of the first rover 802 a and the pluralityof propulsion components 815 b of the second rover 802 b to steer thefirst rover 802 a and/or the second rover 802 b away from the respectivecrater and avoid potential damage to the first rover 802 a and/or thesecond rover 802 b and/or the payload 882.

In some instances, the first rover 802 a and/or the second rover 802 bmay be unable to avoid unevenness in the surface 859. For example, thesurface 859 contains vast stretches of unevenness and the only path tothe respective destination may be through the portions of unevenness. Insuch instances, the first rover 802 a and/or the second rover 802 b maybe configured to autonomously adapt to the unevenness in the surface 859and maintain a ground clearance (e.g., and/or an orientation of thepayload 882 within a range of orientations (e.g., substantially levelwith respect to the surface 859) between the bottom surface of thepayload 882 and the surface 859 to prevent and/or significantly reducepotential collisions between the payload 882 and portions of the (e.g.,lunar) surface 859, as discussed below.

As shown in FIG. 8D, in some instances, the surface 859 may includeunevenness, such as bumps 861 and/or dips 862. In some embodiments, therover suspension system of the first rover 802 a and/or the roversuspension system of the second rover 802 b may be controllable tooperate according to a selected mode. As described previously withrespect to FIGS. 6A-6B, in some embodiments, the suspension system ofthe first rover 802 a and/or the suspension system of the second rover802 b may each be controllable to operate according to a passivesuspension mode or one or more active suspension modes.

For example, as similarly described with respect to FIGS. 6A-6B, in thepassive suspension mode, the ECU of the first rover 802 a and/or the ECUof the second rover 802 b forgo operation of the components of thesuspension system of the first rover 802 a and/or of the second rover802 b (e.g., corresponding to suspension system 310 in FIGS. 3A-3C). Insome embodiments, while the first rover 802 a and the second rover 802 btransport the payload 882 and while employing passive suspension,components of the suspension system of each of the first rover 802 a andthe second rover 802 b may dampen shocks to a given control leg 813a/813 b that may be induced by contacts between a given propulsioncomponent 815 a/815 b and a bump 861 or dip 862 in the terrain 689. Insome such embodiments, the shock absorbed by a given propulsioncomponent 815 a/815 b may be deflected (e.g., for smaller magnitudes ofshock), or absorbed and dissipated (e.g., for greater magnitudes ofshock) by the components (e.g., the spring 336 of the rocker shaft 333in FIGS. 3A-3C) of the suspension system, as described in detailpreviously when referring to FIGS. 6A-6B. However, depending on thegiven propulsion component 815 a/815 b that contacts the bump or dip,the shocks may be deflected unevenly throughout the chassis 803 a/803 b.

Accordingly, the suspension system of the first rover 802 a and/or thesuspension system of the second rover 802 b may each be controllable tooperate according to the one or more active suspension modes to enable amore even deflection of shock throughout the rover chassis 803 a/803 b,and/or to enable maintaining the chassis 803 a/803 b at a levelorientation (e.g., with respect to the surface 859). As describedpreviously with reference to FIGS. 6A-6B, in some embodiments, in theone or more active suspension modes, the ECU of the first rover 802 aand/or the ECU of the second rover 802 b selectively operates one ormore of the components of the suspension system of the first rover 802 aand/or of the second rover 802 b (e.g., corresponding to suspensionsystem 310 in FIGS. 3A-3B). In some embodiments, while the first rover802 a and the second rover 802 b transport the payload 882 and whileemploying active suspension, components of the suspension system of thefirst rover 802 a and/or components of the suspension system of thesecond rover 802 b may be selectively operated to adjust a relativeorientation of a given control leg 813 a/813 b with respect to thesurface 859 when a propulsion component 815 a/815 b coupled to the givencontrol leg 813 a/813 b contacts or is about to contact (e.g., 1 s, 2 s,5 s, 10 s, 15 s, etc. before contacting) a bump or dip in the surface859.

For example, as described previously with respect to FIG. 6B, when agiven propulsion component contacts unevenness in the terrain 859, suchas bump 861 or dip 862, an elevation and/or orientation of the controlleg 813 a/813 b coupled to the given propulsion component 815 a/815 bmay change. For example, in response to a given propulsion component 815a/815 b contacting a dip 862 in the surface 859, an elevation of thecontrol leg 813 a/813 b coupled to the given propulsion component 815a/815 b may decrease with respect to the surface 859 (e.g., due to thelower elevation of the dip 862). In some embodiments, in response to agiven propulsion component contacting the dip 862 in the surface 859, adistance between the control leg 813 a/813 b (e.g., and the givenpropulsion component coupled to the control leg) and the chassis 803a/803 b may increase. In response to a given propulsion component 815a/815 b contacting a bump 861 in the surface 859, an elevation of thecontrol leg 813 a/813 b coupled to the given propulsion component mayincrease with respect to the surface 859 (e.g., due to the higherelevation of the bump 861). In some embodiments, in response to a givenpropulsion component 815 a/815 b contacting the bump 861 in the surface859, the distance between the control leg 813 a/813 b (e.g., and thegiven propulsion component coupled to the control leg) and the chassis803 a/803 b may decrease.

In some embodiments, in response to detecting a change in theorientation of a given control leg 813 a/813 b, the ECU of the rover 802a/802 b may selectively operate the suspension system of the givencontrol leg to adjust an orientation of the control leg 813 a/813 b tothe higher elevation of the bump 861 or the lower elevation of the dip862. For example, as shown in FIG. 8D, the propulsion component 815 a-icontacts the bump 861, which, as described above, causes the control leg813 a-i coupled to the propulsion component 815 a-i to increase inelevation with respect to the surface 859. In response to the increasein elevation of the control leg 813 a-i, the ECU of the first rover 802a may operate the suspension system of the control leg 813 a-i to lowerthe elevation of the control leg 813 a-i with respect to the surface859. The suspension system may be operated according to any of theexemplary processes described previously with respect to FIGS. 6A-6B tochange the orientation of the control leg 813 a-i and raise the controlleg 813 a-i with respect to the surface 859, as shown in FIG. 8D.Additionally, in FIG. 8D, concurrently, the propulsion component 815 b-icontacts the dip 862, which, as described above, causes the control leg813 b-i coupled to the propulsion component 815 b-i to decrease inelevation with respect to the surface 859. In response to the decreasein elevation of the control leg 813 b-i, the ECU of the second rover 802b may operate the suspension system of the control leg 813 b-i to lowerthe elevation of the control leg 813 b-i with respect to the surface859. The suspension system may be operated according to any of theexemplary processes described previously with respect to FIGS. 6A-6B tochange the orientation of the control leg 813 b-i and lower the controlleg 813 b-i with respect to the surface 859, as shown.

In some embodiments, as the ECU of the first rover 802 a and the ECU ofthe second rover 802 b of the second rover 802 b selectively operate thesuspension system of the control leg 815 a-i and the suspension systemof the control leg 813 b-i to adjust an orientation of each of thecontrol leg 813 a-i and the control leg 813 b-i to maintain the chassis803 a of the first rover 802 a and the chassis 803 b of the second rover802 b each within an orientation that is (e.g., substantially) levelwith respect to the ground, the ECU of the first rover 802 a may (e.g.,continuously) communicate with the ECU of the second rover 802 b toselectively change the speed at which the first rover 802 a and thesecond rover 802 b are traveling. For example, while the first rover 802a and the second rover 802 b individually adjust orientations of theirrespective control legs (e.g., 813 a-i and 813 b-i), the speeds at whichthe first rover 802 a and the second rover 802 b may change to betterenable the first rover 802 a and/or the second rover 802 b to adjustchassis orientation with respect to the surface 859, while alsomaintaining the payload 882 within an orientation that is substantiallylevel with respect to the surface 859. For example, the ECU of the firstrover 802 a may selectively reduce the speed (e.g., by 0.5 m/s, 1 m/s,1.5 m/s, 2 m/s, 3 m/s, etc.) at which the first rover 802 a is traveling(e.g., via the motor assembly coupled to each of the propulsioncomponents 815 a) to allow the control leg 813 a-i to adjust itsorientation as the propulsion component 815 a-i contacts the bump 861.The ECU of the first rover 802 a may concurrently communicate with theECU of the second rover 802 b to cause the ECU of the second rover 802 bto selectively reduce the speed at which the second rover 802 b istraveling (e.g., by a same amount that the speed of the first rover 802a is reduced (e.g., by 0.5 m/s, 1 m/s, 1.5 m/s, 2 m/s, 3 m/s, etc.)).Additionally or alternatively, in some embodiments, the ECU of thesecond rover 802 b may communicate with the ECU of the first rover 802 ato cause the ECU of the first rover 802 a to selectively reduce thespeed at which the first rover 802 a is traveling (e.g., by a sameamount that the speed of the second rover is reduced). The coordinatedreduction in traveling speed when at least one of the first rover 802 aand the second rover 802 b comes into contact with unevenness in theterrain 859 may thus prevent or significantly reduce the likelihood ofthe first portion and/or the second portion of the payload 882 becomingunattached from the chassis 803 a of the first rover 802 a and/or thechassis 803 b of the second rover 802 b.

Thus, as shown in FIG. 8D, the respective suspension systems of thecontrol leg 813 a-i and the control leg 813 b-i may be selectivelyoperated to autonomously adapt the orientations (e.g., elevations) ofthe control legs 813 a-i and 813 b-i to unevenness in the terrain. Inthis way, the chassis 803 a of the first rover 802 a and the chassis 803b of the second rover 802 b may remain (substantially (e.g., within 2,5, 10, 15, 20, 25, or 30 degrees of being)) level (e.g., about 0 degreesas measured along a surface (e.g., the top surface) of the medial memberof each rover chassis 803 a/803 b (e.g., corresponding to medial member207 in FIGS. 2A-2B)) with respect to a reference (e.g., the surface 859,or gravity) and maintain a ground clearance (e.g., and/or an orientationof the payload 882 within a range of orientations (e.g., substantiallylevel with respect to the surface 859) between the bottom surface of thepayload 882 and the unevenness in the surface (e.g., the bumps 861 anddips 862) to prevent and/or diminish impacts between the payload 882 andthe surface 859. Thus, one advantage of the passive and activesuspension modes of the rover suspension system during a transportationof a large payload is that the large payload may be safeguarded fromdamage during transport.

In some embodiments, once the first rover 802 a and the second rover 802b arrive at the respective destination, the ECU of the first rover 802 amay communicate with the ECU of the second rover 802 b to concurrentlylower the chassis 803 a of the first rover 802 a and the chassis 803 bof the second rover 802 b with respect to the surface 859 (e.g.,according to the example processes described with reference to FIGS.5A-5H). In some embodiments, once the ECU of the second rover 802 b hasdetermined that the chassis 803 b of the second rover 802 b has beenlowered with respect to the surface 859, such that a bottom surface ofthe second portion of the payload 882 is in contact with the surface859, the ECU of the second rover 802 b may send one or more signals tothe ECU of the first rover 802 a to convey that the second portion ofthe payload 882 is in contact with the surface 859. Once the ECU of thefirst rover 802 a has determined that the chassis 803 a of the firstrover 802 a has been lowered with respect to the surface 859, such thata bottom surface of the first portion of the payload 882 is in contactwith the surface 859, and after receiving the one or more signals fromthe ECU of the second rover 802 b, the ECU of the first rover 802 a maycommunicate one or more commands to the ECU of the second rover 802 b(e.g., via their respective communications antennas 812 a and 812 b) totrigger the ECU of the second rover 802 b to initiate release of thesecond portion of the payload 882 when the ECU of the first rover 802 aconcurrently initiates release of the first portion of the payload 882.In some embodiments, the latch assembly of the first rover 802 a and thelatch assembly of the second rover 802 b may be concurrently operated(e.g., by their respective rover ECUs) to cause the plurality of hooksof the chassis 803 a of the first rover 802 a to disengage from thefirst portion (e.g., the first end) of the payload 882 and the pluralityof hooks of the chassis 803 b of the second rover 802 b to disengagefrom the second portion (e.g., the second end) of the payload 882,thereby depositing the payload 882 at the respective location. Thesystem comprising the first rover 802 a and the second rover 802 b maythen be utilized to retrieve a second payload or perform another actionas instructed by their respective rover ECUs (e.g., returning to a lunaroutpost or lander).

FIG. 9 illustrates another example retrieval of a large payload 982using a multi-rover system according to some embodiments of thedisclosure. In some embodiments, the multi-rover system optionallycorresponds to system 150 shown previously in FIG. 1B. In someinstances, the payload 982 may be too large (e.g., in size and/or shape)and/or too heavy for one or even two rovers (e.g., first rover 802 a andsecond rover 802 b in FIGS. 8A-8D) to successfully retrieve, transportand/or deposit the payload 982. As shown in FIG. 9 , for example, thepayload 982 may be a planetary lander (e.g., a lunar lander).Accordingly, the multi-rover system may be provided with a suitableplurality of rovers for the secure and efficient retrieval,transportation and/or deposition of the large payload 982.

As shown in FIG. 9 , the multi-rover system may include a first rover902 a, a second rover 902 b, a third rover 902 c and a fourth rover 902d. In some embodiments, the first rover 902 a, the second rover 902 b,the third rover 902 c and the fourth rover 902 d optionally eachcorrespond to the rover 202/502/602 shown previously in FIGS. 2A-2B,5A-5H, and 6A-6B, respectively. As discussed previously with referenceto FIG. 1B, the respective ECUs of the first rover 902 a, the secondrover 902 b, the third rover 902 c, and the fourth rover 902 d may beconfigured to communicate via their respective communications units. Forexample, as discussed below, the ECU of the first rover 902 a, the ECUof the second rover 902 b, the ECU of the third rover 902 c, and the ECUof the fourth rover 902 d may be configured to communicate with via acommunications link connecting their respective communications units toperform joint actions involving the large payload 982.

As shown in FIG. 9 , the planetary lander 982 may comprise a pluralityof legs including a first leg 949 a, a second leg 949 b, a third leg 949c and a fourth leg 949 d. The plurality of legs 949 a-949 d may becoupled to a plurality of pads in contact with the surface (e.g., thelunar surface) on which the payload 982 is placed. For example, as shownin FIG. 9 , the second leg 949 b of the planetary lander 982 may becoupled to a pad 946 b and the third leg 949 c of the planetary lander982 may be coupled to a pad 946 c. As described below, the multi-roversystem may be utilized to retrieve, transport and/or deposit theplanetary lander 982 by configuring the plurality of rovers 902 a-902 dto attach to the plurality of legs 949 a-949 d as effective anchorpoints.

As discussed above with reference to FIGS. 8A-8D, in some embodiments,the plurality of rovers 902 a-902 d may be configured to locate theplanetary lander 982. For example, each rover of the plurality of rovers902 a-902 d may utilize their respective sensors (e.g., the one or moresensors 820 a-820 b shown in FIGS. 8A-8D) to identify the payload 982.Particularly, in some embodiments, each rover of the plurality of rovers902 a-902 d may be configured to identify a respective portion of thepayload 982 to which the rover will attach. For example, the first rover902 a may identify the first leg 949 a as a target for attachment, thesecond rover 902 b may identify the second leg 949 b as a target forattachment, the third rover 902 c may identify the third leg 949 c as atarget for attachment, and the fourth rover 902 d may identify thefourth leg 949 d as a target for attachment. The respective ECUs of theplurality of rovers 902 a-902 d may communicate (e.g., via theirrespective antennas 912 a-912 d) to coordinate movement of the pluralityof rovers 902 a-902 d toward the targeted plurality of legs 949 a-949 dof the planetary lander 982. As discussed herein with respect to FIGS.8A-8D, each ECU of a given rover of the plurality of rovers 902 a-902 dmay operate the plurality of propulsion components (e.g., propulsioncomponents 815 a/815 b) of the given rover (e.g., via a motor assemblyassociated with each propulsion component) to cause the given rover tomove toward a respective leg of the planetary lander 982. In someembodiments, the plurality of rovers 902 a-902 d may concurrentlyapproach the targeted plurality of legs 949 a-949 d of the planetarylander 982 to initiate retrieval of the planetary lander 982.

In some embodiments, as discussed above, the plurality of rovers 902a-902 d may be positioned above the plurality of pads (e.g., 946 b, 946c) of the planetary lander 982, such that the chassis of each rover atleast partially surrounds a portion of a corresponding leg of theplanetary lander 982. As an illustrative example, the second rover 902 bmay be driven toward the second leg 949 b of the planetary lander 982until the chassis 903 b (e.g., the medial member of the chassis) of thesecond rover 902 b is positioned above the pad 946 b, such that theinterior portions of the chassis 903 b of the second rover 902 b atleast partially surround the second leg 949 b of the planetary lander982. Each rover of the plurality of rovers 902 a-902 b may be positionedwith respect to the planetary lander 982 in this way, as shown in FIG. 9.

In some embodiments, as discussed above, when each rover of theplurality of rovers 902 a-902 d is positioned above a corresponding legof the plurality of legs 949 a-949 b of the planetary lander 982, therespective ECUs of the plurality of rovers 902 a-902 d may communicateto initiate coordinated retrieval of the planetary lander 982. Forexample, the respective ECUs of the plurality of rovers 902 a-902 d maycommunicate to latch with the plurality of legs 949 a-949 d of theplanetary lander 982. As an illustrative example, the ECU of the firstrover 902 a may selectively control the plurality of control legs (e.g.,control legs 813 a/813 b in FIGS. 8A-8D) to cause the chassis 903 a ofthe first rover 902 a to be lowered (e.g., via a suspension system ofeach control leg) with respect to the surface on which the planetarylander 982 is placed. Each rover of the plurality of rovers 902 a-902 dmay be lowered in this way to lower the chassis of each rover withrespect to the surface on which the planetary lander 982 is placed toposition the chassis of each rover to surround a portion of each leg ofthe planetary lander 982.

As described above with reference to FIGS. 8A-8D, in some embodiments,when the chassis of each rover of the plurality of rovers 902 a-902 dare lowered such that the chassis of each rover is within a thresholddistance (e.g., abutting a top surface of the leg of the planetarylander 982 or within 2 cm, 5 cm, 7 cm, 10 cm, 15 cm, etc. above the topsurface of the leg) of a corresponding leg of the planetary lander 982,the respective ECUs of the plurality of rovers 902 a-902 d maycommunicate to initiate coordinated latching with respective portions ofthe planetary lander 982. In some embodiments, the ECU of each rover ofthe plurality of rovers 902 a-902 d may operate a latch system (e.g.,corresponding to latch system 506 in FIGS. 5F-5H) of each rover to causethe chassis of each rover to become attached to a portion of a leg ofthe planetary lander that is below the chassis. For example, a pluralityof hooks of the latch system of each rover may be operated by each roverECU to protrude from the interior portions of the chassis of each roverto engage with and/or grip a portion of the leg of the planetary landerthat is below the chassis. As described above with reference to FIGS.8A-8D, the plurality of hooks may be configured (e.g., in shape and/orby coating/lining) to grip a portion of each leg of the planetary lander982. Thus, the planetary lander 982 may be configured to be transportedvia the coordinated transportation of the plurality of legs 949 a-949 dattached to the plurality of rovers 902 a-902 d.

In some embodiments, as described previously herein, following theretrieval of the payload 982, the respective ECUs of the plurality ofrovers 902 a-902 d may initiate coordinated processes for transportingand/or depositing the payload 982. For example, the ECU of each rovermay operate the control legs of each rover (e.g., via the suspensionsystem of each control leg) to change respective orientations of eachcontrol leg of each of the plurality of rovers 902 a-902 d to graduallyand concurrently raise the respective chassis 903 a-903 d of theplurality of rovers 902 a-902 d and the plurality of legs 949 a-949 dattached to the respective chassis 903 a-903 d, and to thus raise theplanetary lander 982 with respect to the surface on which the planetarylander 982 is placed.

In some embodiments, the respective ECUs of the plurality of rovers 902a-902 b may communicate to coordinate operation of the plurality ofpropulsion components (e.g., 815 a/815 b in FIGS. 8A-8D) of each of theplurality of rovers 902 a-902 d (e.g., by driving a corresponding motorassembly coupled to each propulsion component) to concurrently cause amovement (e.g., at a same speed (e.g., 1 m/s, 2 m/s, 2.5 m/s, 3.5 m/s, 5m/s, 8 m/s, 10 m/s, etc.)) of each rover of the plurality of rovers 902a-902 d and the payload 882 to a respective location on the surfacewhile the chassis 903 a-903 d of the plurality of rovers 902 a-902 d areeach in the raised position, as shown in FIG. 9 . In some embodiments,as described above with reference to FIGS. 8A-8D, the respective ECUs ofthe plurality of rovers 902 a-902 b may communicate to selectively adaptthe plurality of rovers 902 a-902 d to unevenness in the surface duringtransport of the planetary lander 982. For example, each rover of theplurality of rovers 902 a-902 d may be operable to adjust an orientationof one or more of its control legs (e.g., control legs 813 a-i/813 b-iin FIG. 8D) to adapt to bumps (e.g., 861) and/or dips (e.g., 862) in thesurface to maintain the plurality of legs 949 a-949 d of the planetarylander 982 within an orientation that is substantially (e.g., within 2,5, 10, 15, 20, 25, or 30 degrees of being) level with respect to thesurface, thus preventing and/or significantly reducing potential damageto the planetary lander 982. At the respective location, for example,the chassis 903 a-903 d of the plurality of rovers 902 a-902 d may againbe concurrently lowered with respect to the lunar surface (e.g.,according to the example processes described above), and the latchsystem of each of the plurality of rovers 902 a-9902 b may be actuatedto cause the plurality of hooks of the latch system to disengage fromeach leg of the plurality of legs 949 a-949 d of the planetary lander982, thereby depositing the planetary lander at the respectivedestination.

Therefore, as outlined above with reference to FIG. 9 , the multi-roversystem (e.g., corresponding to system 150 in FIG. 1B) may be adapted toenable the retrieval, transportation and/or deposition of large payloadsby providing an increased number of rovers configured to communicate toindividually and jointly perform actions including the large payloads.

Contingency Operations and Associated Processes

FIG. 10 illustrates an example contingency operation using a roveraccording to some embodiments of the disclosure. In some embodiments,the rover described herein above may be configurable to performcontingency operations. In some instances, a respective rover may becomeimmobile due to power outages or power failure (e.g., due to shortagesin the rover battery supply or component (e.g., ECU) failure),rover/component damage (e.g., damage incurred by one or more propulsioncomponents (e.g., corresponding to propulsion components 215 in FIGS.2A-2B) of the respective rover, hardware malfunction (e.g., malfunctionor misfire of the suspension system components (e.g., corresponding tosuspension system 310 in FIGS. 3A-3C) or the motor assembly components(e.g., corresponding to motor assembly 322 in FIG. 3A)), and the like.As shown in FIG. 10 , for example, the rover 1002 b may be immobile.Accordingly, a second rover may be utilized to retrieve and transport(e.g., to tow) the immobile respective rover, as described below. Insome embodiments, the second rover and the immobilized respective rovermay form a multi-rover system during performance of the contingencyoperation.

As shown in FIG. 10 , the multi-rover system may include a first rover1002 a and a second rover 1002 b. In some embodiments, the multi-roversystem optionally corresponds to system 150 shown previously in FIG. 1B.In some embodiments, the first rover 1002 a may correspond to the rover202/502/602 shown previously in FIGS. 2A-2B, 5A-5H, and 6A-6B,respectively, and the second rover 1002 b may correspond to rover 702shown in FIG. 7C. For example, the second rover 1002 b may be configuredas a rover vehicle operable by one or more users (e.g., astronauts)1071. As mentioned above, the second rover 1002 b may be immobilized.The first rover 1002 a may be utilized to perform a contingencyoperation (e.g., search and rescue of the one or more users 1071)involving the second rover 1002 b. As discussed previously withreference to FIG. 1B, the ECU of the first rover 1002 a may beconfigured to communicate with the ECU of the second rover 1002 b viatheir respective communications units (e.g., corresponding tocommunications units 116 a and 116 b in FIG. 1B). For example, asdiscussed below, the ECU of the first rover 1002 a may be configured tocommunicate with the ECU of the second rover 1002 b via a communicationslink connecting their respective communications units to conduct theretrieval and transportation of the immobilized second rover 1002 b.

As an illustrative example, the second rover 1002 b may be immobilizeddue to component failure of one or more of the propulsion components1015 b (e.g., due to hardware malfunction of the motor assemblyassociated with the one or more propulsion components 1015 b) of thesecond rover 1002 b. For example, the electrical capabilities of the ECU(e.g., the communications capabilities and control of the suspensionsystems of the control legs 1013 b) of the second rover 1002 b may bemaintained. In some embodiments, the first rover 1002 a may, via the oneor more sensors 1020, detect and identify a location of the second rover1002 b. In some embodiments, the ECU of the first rover 1002 a mayoperate the propulsion components 1015 a (e.g., via a motor assemblyassociated with each propulsion component 1015 a) to approach the secondrover 1002 b. In some embodiments, the first rover 1002 b optionallycommunicates with the second rover 1002 b using their respectiveantennas 1012 a and 1012 b (e.g., in communication with their respectivecommunications units) to further enable the first rover 1002 a to detectand identify the location of the second rover 1002 b.

In some embodiments, as the first rover 1002 a is driven toward thesecond rover 1002 b, the ECU of the first rover may utilize data (e.g.,image data) captured via the one or more sensors 1020 to positionchassis 1003 a of the first rover 1002 a in front of the chassis 1003 bof the second rover 1002 b. In some embodiments, when the chassis 1003 aof the first rover 1002 a is positioned in front of the chassis 1003 bof the second rover 1002 b, the plurality of propulsion components 1015a of the first rover 1002 a optionally cease to be driven, such that thefirst rover 1002 a may remain stationary in front of the second rover1002 b. In some embodiments, the first rover 1002 a may cease drivingtoward the second rover 1002 b when the ECU of the first rover 1002 adetects that a respective portion of the chassis 1003 a (e.g., a centerportion of the medial member of the chassis 1003 a) of the first rover1002 a is within a threshold distance (e.g., 1 m, 2 m, 3 m, 4.5 m, 5 m,5.5 m, 7 m, 10 m, etc.) of a respective portion of the chassis 1003 b(e.g., a center portion of the medial member of the chassis 1003 b) ofthe second rover 1002 b.

In some embodiments, as shown in FIG. 10 , the chassis 1003 a of thefirst rover 1002 a may be configured to be connected to the chassis 1003b of the second rover 1002 b to transport the second rover 1002 b andthe one or more users 1071 to safety. For example, as shown, aconnection interface may be attached to the chassis 1003 b of the secondrover 1002 b. In some embodiments, the connection interface 1084 isattached to the chassis 1003 b by the one or more users 1071. In someembodiments, the connection interface 1084 is already provided on thechassis 1003 b of the second rover 1002 b prior to the second rover 1002b being immobilized. In some embodiments, a line 1085 may be connectedto the connection interface 1084 to connect the chassis 1003 a of thefirst rover 1002 a to the chassis 1003 b of the second rover 1002 b. Forexample, the line 1085 may include a cable/wire and a hooking element(e.g., a hook or clip) configured to securely connect to the connectioninterface 1084. In some embodiments, the line 1085 may be connected tothe connection interface 1084 by the one or more users 1071.

In some embodiments, when the chassis 1003 a of the first rover 1002 ais connected to the chassis 1003 b of the second rover 1002 b (e.g., vialine 1085), the first rover 1002 a may be operated to transport (e.g.,tow) the second rover 1002 b and the one or more users 1071 to safety.For example, the ECU of the first rover 1002 a may operate the pluralityof propulsion components 1015 a to cause a movement of the first rover1002 a and thus a movement of the second rover 1002 b (e.g., via apulling motion between the first rover 1002 a and the second rover 1002b). In some embodiments, while the first rover 1002 a transports thesecond rover 1002 b, the ECU of the first rover 1002 a may communicatewith the ECU of the second rover 1002 b (e.g., via their respectiveantennas 1012 a and 1012 b) to coordinate adaptive motion of the firstrover 1002 a. For example, the ECU of the first rover 1002 a may detect,via the one or more sensors 1020, that unevenness (e.g., bumps or dips)in the surface is present and may steer the first rover 1002 a to avoidand/or limit contact with the unevenness in the surface (e.g., accordingto the processes described above with reference to FIGS. 6A-6B). Asanother example, the ECU of the first rover 1002 a may communicate withthe ECU of the second rover 1002 b to coordinate determination of arespective speed at which the first rover 1002 a may pull the secondrover 1002 b. The respective speed, for example, may be determined basedon a weight of the second rover 1002 b, including the modular payload1052 attached to the chassis 1003 b of the second rover 1002 b and theone or more users 1071 riding on the second rover 1002 b. In someembodiments, the ECU of the second rover 1002 b may communicateinformation including the weight determination (e.g., and/or otherinformation) to the ECU of the first rover 1002 a to coordinate therespective speed at which the first rover 1002 a may pull the secondrover 1002 b. The respective speed determined based on such factors mayallow the first rover 1002 a to be driven (e.g., at 1 m/s, 2 m/s, 2.5m/s, 3.5 m/s, 5 m/s, 8 m/s, 10 m/s, etc.) fast enough to pull and causemovement of the second rover 1002 b, while maintaining separationbetween the first rover 1002 a and the second rover 1002 b (e.g., toprevent a collision between the first rover 1002 a and the second rover1002 b) during transport. In some embodiments, the first rover 1002 amay be configured to share and/or supply power with the second rover1002 b for use in powering the ECU of the second rover 1002 b. Forexample, the first rover 1002 a may supply power to the second rover1002 b via the line 1085 (e.g., which may include conductive material)or via a different means (e.g., a power cable connected between thepower system of the first rover 1002 a and the power system of thesecond rover 1002 b (e.g., corresponding to power systems 108 a and 108b in FIG. 1B)).

Thus, as discussed above, a rover (and/or additional rovers) may beconfigurable to perform contingency operations, such as the retrievaland transport of an immobilized rover. Additionally or alternatively, insome embodiments, the first rover 1002 a may also be configured as arover vehicle (e.g., corresponding to rover 702 in FIG. 7 and describedabove). In some such embodiments, the one or more users 1071 may operatethe first rover 1002 a (e.g., according to the processes described abovewith reference to FIG. 7C) to drive the first rover 1002 a and transportthe second rover 1002 b connected to the first rover 1002 a to safety.

It should be understood that additional contingency operations may beperformed using the multi-rover system disclosed herein. For example, aplurality of rovers (e.g., two or more rovers) may be utilized tojointly tow a larger vehicle that is not another rover (e.g., such as atraditional lunar roving vehicle (LRV)). As another example, a pluralityof rovers (e.g., two or more rovers) may be utilized to concurrently andindividually transport and deposit a corresponding plurality of modularpayloads. Other examples involving coordinated motion and action of aplurality of rovers are possible.

Rover Operation of Diverse Payloads

Attention is now directed towards examples of operable payloads (e.g.,functional modules) that are configured to interface with a chassis of arover. When interfaced with the chassis of the rover, the rover ECU mayselectively communicate with the functional modules to perform one ormore actions involving the functional modules, as described below.

FIGS. 11A-11E illustrate examples of functional modules 1172 a-1172 econfigured to interface with a rover 1102 according to some embodimentsof the disclosure. In some embodiments, the rover 1102 optionallycorresponds to rover 702, 602, 502, and/or 202 shown in FIGS. 7A-7E,FIGS. 6A-6B, FIGS. 5A-5H, and/or FIGS. 2A-2B, respectively. As describedherein, the rover may be configured to retrieve, transport, and/ordeposit payloads on a surface (e.g., a lunar surface). In someembodiments, the rover may be configurable to perform one or moreadditional actions and/or functions by interfacing the rover with arespective functional module, as described below.

In some embodiments, the rover 1102 may be configured as a sciencemobility system, as described previously with reference to FIGS. 7A-7B.In some such embodiments, as shown in FIG. 11A, the surface sciencefunctional module 1166 may be interfaced with the medial member (e.g.,medial member 707 in FIG. 7D) of the rover chassis 1103. As discussedabove, the surface science functional module 1166 may include the remotemast 1167 (e.g., and a robotic arm (e.g., 768 in FIG. 7D)) for use inperforming scientific mission objectives. In some embodiments, thesurface science functional module may configure the rover to (e.g.,autonomously or via external control) interface with and perform one ormore respective actions involving a (e.g., second) respective functionalmodule. It should be understood that, in some embodiments, the rover1102 may be configured to perform the one or more respective actionsinvolving the respective functional module without the surface sciencefunctional module 1166 attached to the medial member of the chassis 1103(e.g., as shown in FIG. 11E).

In some embodiments, the chassis of the rover may be configured tophysically and communicatively interface with the respective functionalmodule for performing one or more drilling operations. For example, asshown in FIG. 11A, the rover 1102 may be interfaced with the respectivefunctional module 1172 a. In some embodiments, the respective functionalmodule 1172 a may include a drilling system including a drill 1173configured to perform the one or more drilling operations. As shown inFIG. 11A, the respective functional module 1172 a may be attached to thechassis 1103 of the rover 1102, such that the interior portions 1101 ofthe chassis 1103 at least partially surround the respective functionalmodule 1172 a. In some embodiments, the respective functional module1172 a may be configured to attach to the chassis 1103 of the rover 1102via a plurality of attachment elements (not shown) disposed on one ormore sides of the respective functional module 1172 a. For example, theplurality of attachment elements may correspond to a plurality of latchreceptacles. In some embodiments, the plurality of attachment elementsmay correspond to the plurality of latch receptacles of the modularpayload described herein (e.g., the same sizes, placements, relativespatial arrangements, and/or orientations as latch receptacles 454 ofthe modular payloads 452 a-452 b in FIG. 4 ). Accordingly, the rover1102 may be configured to retrieve the respective functional module 1172a according to any of the processes described previously with referenceto FIGS. 5A-5H. For example, the chassis 1103 may attach to theplurality of attachment elements of the respective modular payload 1172a via the plurality of hooks of the latch system of the rover (e.g.,plurality of hooks 553 of the latch system 506 in FIGS. 5F-5H). Asdescribed above with reference to FIGS. 5A-5H, the rover ECU (e.g.,corresponding to ECU 104 in FIG. 1A) may utilize image data captured viathe one or more sensors 1120 (e.g., corresponding to the one or moresensors 520 in FIGS. 5A-5E) to locate and position the chassis 1103above the respective functional module 1172 a.

In some embodiments, the ECU of the rover 1102 may be configured tocommunicate with the drilling system of the respective functional module1172 a to selectively operate the drill 1173. For example, when therespective functional module 1172 a is attached to the chassis 1103(e.g., via the latch system discussed above), the ECU of the rover 1102may become communicatively (e.g., electrically) coupled to (e.g., aprocessor of) the drilling system of the respective functional module1172 a. For example, a top surface of the respective functional module1172 a may include conductive pads, traces, plugs, etc. configured tocontact one or more conductive elements disposed on a bottom surface ofthe medial member (e.g., medial member 207 in FIGS. 2A-2B) of thechassis 1103 to form a communication link between the rover ECU and thedrilling system. Additionally or alternatively, in some embodiments, therover ECU may be configured to communicate wirelessly (e.g., via thecommunications unit 116 in FIG. 1A) with the drilling system of therover 1102 to form the communication link between the rover ECU and thedrilling system.

As mentioned above, when the respective functional module 1172 a isattached to the chassis 1103 of the rover 1102, the ECU of the rover maycause the rover 1102 and/or the respective functional module 1172 a toperform one or more drilling operations at a respective location on the(e.g., lunar) surface. For example, the one or more drilling operationsmay include drilling a hole into the surface on which the plurality ofpropulsion components 1115 of the rover 1102 are placed. When the ECUdetermines that the respective functional module 1172 a is attached tothe chassis 1103 of the rover 1102 (e.g., that the plurality of hookshave engaged with the plurality of attachment elements), the rover ECUmay selectively operate the plurality of propulsion components 1115(e.g., via the motor assembly (e.g., such as motor assembly 522 in FIG.5A) coupled to each propulsion component) to cause a motion of each ofthe propulsion components 1115 and a movement of the rover 1102 and therespective functional module 1172 a attached to the chassis 1103 of therover 1102 in a respective direction toward the location at which thedrilling will occur. When the rover 1102 reaches the respective locationon the surface, the rover ECU may operate the plurality of propulsioncomponents 1115 and/or the plurality of control legs 1113 of the rover1102 to position the drill 1173 above a particular portion of thesurface at the respective location into which the hole is to be drilled.For example, when the rover ECU operates the plurality of propulsioncomponents 1115 and/or the plurality of control legs 1113 of the rover1102, the rover ECU may utilize image data captured via the one or moresensors 1120 to locate and position the drill 1173 above the particularportion of the surface. When the ECU of the rover 1102 determines thatthe drill 1173 is positioned above the particular portion on thesurface, the ECU may communicate with the drill system of the respectivefunctional module 1172 a to operate the drill 1173 and perform thedrilling operation using the drill 1173.

In some embodiments, the chassis of the rover may be configured tophysically and communicatively interface with the respective functionalmodule for performing one or more cable/tubing deployment operations.For example, as shown in FIG. 11B, the rover 1102 may be interfaced witha second respective functional module 1172 b. In some embodiments, thesecond respective functional module 1172 b may include a deploymentsystem including a roller 1174 having cable/tubing configured to performthe one or more cable/tubing deployment operations. As shown in FIG.11B, the second respective functional module 1172 b may be attached tothe chassis 1103 of the rover 1102, such that the interior portions ofthe chassis 1103 at least partially surround the second respectivefunctional module 1172 b. As discussed above with reference to FIG. 11A,in some embodiments, the second respective functional module 1172 b maybe configured to attach to the chassis 1103 of the rover 1102 via aplurality of attachment elements (not shown). For example, the pluralityof attachment elements may correspond to a plurality of latchreceptacles. In some embodiments, the plurality of attachment elementsmay correspond to the plurality of latch receptacles of the modularpayload described herein (e.g., the same sizes, placements, relativespatial arrangements, and/or orientations as latch receptacles 454 ofthe modular payloads 452 a-452 b in FIG. 4 ). Accordingly, the rover1102 may be configured to retrieve the second respective functionalmodule 1172 b according to any of the processes described previouslywith reference to FIGS. 5A-5H.

In some embodiments, the ECU of the rover 1102 may be configured tocommunicate with the deployment system of the second respectivefunctional module 1172 b to selectively operate the roller 1174. Forexample, when the second respective functional module 1172 b is attachedto the chassis 1103 (e.g., via the latch system, as discussed above),the ECU of the rover 1102 may become communicatively (e.g.,electrically) coupled to (e.g., a processor of) the deployment system ofthe second respective functional module 1172 b. As discussed above withreference to FIG. 11A, a (e.g., wired or wireless) communication linkmay be established between the rover ECU and the deployment system ofthe second respective functional module 1172 b.

As mentioned above, when the second respective functional module 1172 bis attached to the chassis 1103 of the rover 1102, the ECU of the rovermay cause the rover 1102 and/or the second respective functional module1172 b to perform one or more cable/tubing deployment operations over arespective region of the (e.g., lunar) surface. For example, the one ormore cable/tubing deployment operations may include deploying thecable/tubing between a first respective location and a second respectivelocation on the surface on which the plurality of propulsion components1115 of the rover 1102 is placed. A first end of the cable/tubing may befixed at the first respective location on the surface. In someembodiments, the second respective functional module 1172 b may beretrieved at the first respective location on the surface. When the ECUdetermines that the second respective functional module 1172 b isattached to the chassis 1103 of the rover 1102 (e.g., that the pluralityof hooks have engaged with the plurality of attachment elements), therover ECU may selectively operate the plurality of propulsion components1115 to cause a motion of each of the propulsion components 1115 and amovement of the rover 1102 and the second respective functional module1172 b attached to the chassis 1103 of the rover 1102 in a respectivedirection toward the second respective location at which a second end ofthe cable/tubing will be deployed. As the rover 1102 travels toward thesecond respective location, the rover ECU may communicate with thedeployment system of the second respective functional module 1172 b tooperate the roller 1174. For example, the roller 1174 may be motorizedand may be operated to cause a (e.g., counterclockwise) rotation of theroller 1174 to increase an amount of the cable/tubing that is placedonto the surface. Additionally or alternatively, in some embodiments,the roller 1174 may be unmotorized, and the roller 1174 may be caused torotate as a distance between the rover 1102 and the first respectivelocation increases (e.g., due to a pulling of the cable/tubing wrappedaround the roller 1174).

When the rover 1102 reaches the second respective location on thesurface (e.g., using image data captured via the one or more sensors1120), the rover ECU may operate the plurality of propulsion components1115 and/or the plurality of control legs 1113 of the rover 1102 todeposit the second respective functional module 1172 b at the secondrespective location on the surface. For example, the rover ECU may ceasedriving the plurality of propulsion components 1115 and may changerespective orientations of the plurality of control legs to cause thechassis 1103 to be lowered toward the surface to deposit the secondrespective functional module on the surface. The rover ECU may controlthe latch system of the rover 1102 to cause the plurality of hooks ofthe latch system to disengage from the plurality of attachment elementsof the second respective functional module 1172 b, and to deposit thesecond respective functional module 1172 b, and thus the cable/tubing,at the second respective location on the surface.

In some embodiments, the chassis of the rover may be configured tophysically and communicatively interface with the respective functionalmodule for performing one or more surface excavation operations. Forexample, as shown in FIG. 11C, the rover 1102 may be interfaced with athird respective functional module 1172 c. In some embodiments, thethird respective functional module 1172 c may include an excavationsystem including a blade 1175 configured to perform the one or moresurface excavation operations. As shown in FIG. 11C, the thirdrespective functional module 1172 c may be attached to the chassis 1103of the rover 1102, such that the interior portions of the chassis 1103at least partially surround the third respective functional module 1172c. As discussed above with reference to FIG. 11A, in some embodiments,the third respective functional module 1172 c may be configured toattach to the chassis 1103 of the rover 1102 via a plurality ofattachment elements (not shown). For example, the plurality ofattachment elements may correspond to a plurality of latch receptacles.In some embodiments, the plurality of attachment elements may correspondto the plurality of latch receptacles of the modular payload describedherein (e.g., the same sizes, placements, relative spatial arrangements,and/or orientations as latch receptacles 454 of the modular payloads 452a-452 b in FIG. 4 ). Accordingly, the rover 1102 may be configured toretrieve the third respective functional module 1172 c according to anyof the processes described previously with reference to FIGS. 5A-5H.

In some embodiments, the ECU of the rover 1102 may be configured tocommunicate with the excavation system of the third respectivefunctional module 1172 c to selectively operate the blade 1175. Forexample, when the third respective functional module 1172 c is attachedto the chassis 1103 (e.g., via the latch system, as discussed above),the ECU of the rover 1102 may become communicatively (e.g.,electrically) coupled to (e.g., a processor of) the excavation system ofthe third respective functional module 1172 c. As discussed above withreference to FIG. 11A, a (e.g., wired or wireless) communication linkmay be established between the rover ECU and the excavation system ofthe third respective functional module 1172 c.

As mentioned above, when the third respective functional module 1172 cis attached to the chassis 1103 of the rover 1102, the ECU of the rovermay cause the rover 1102 and/or the third respective functional module1172 c to perform one or more surface excavation operations at arespective location on the (e.g., lunar) surface. For example, the oneor more surface excavation operations may include site preparation(e.g., pushing and/or flattening soil, rocks, and other material) on thesurface on which the plurality of propulsion components 1115 of therover 1102 is placed. When the ECU determines that the third respectivefunctional module 1172 c is attached to the chassis 1103 of the rover1102 (e.g., that the plurality of hooks have engaged with the pluralityof attachment elements), the rover ECU may selectively operate theplurality of propulsion components 1115 to cause a motion of each of thepropulsion components 1115 and a movement of the rover 1102 and thethird respective functional module 1172 c attached to the chassis 1103of the rover 1102 in a respective direction toward the respectivelocation at which the surface excavation will be performed.

When the rover 1102 reaches the respective location on the surface, therover ECU may communicate with the excavation system of the thirdrespective functional module 1172 c to operate the blade 1175. Forexample, the excavation system may be operable to cause the blade 1175to be selectively lowered toward the surface and/or to be tilted (e.g.,angled upward or downward) with respect to the surface, such that theblade 1175 may engage with the surface. In some embodiments, theexcavation system may be operable to cause the blade 1175 to beselectively raised away from the surface (e.g., for pushing and/orflattening tall and/or elevated objects (e.g., boulders, bumps, etc.).In some embodiments, the rover ECU may communicate with the suspensionsystem (e.g., corresponding to suspension system 310 in FIGS. 3A-3C) ofeach of the plurality of control legs 1113 to cause the plurality ofcontrol legs 1113 to selectively change their respective orientations(e.g., with respect to the surface) to raise or lower the chassis 1103of the rover 1102, and thus correspondingly raise or lower the blade1175 of the third respective functional module 1172 c. The rover ECU mayoperate the plurality of propulsion components 1115 to produce a forwardmotion of the rover 1102 and to cause the blade 1175 to push and/orflatten surface material at the respective location on the surface.

In some embodiments, the chassis of the rover may be configured tointerface with one or more respective functional modules for performingone or more solar farm deployment operations. For example, as shown inFIG. 11D, the rover 1102 may be interfaced with one or more fourthrespective functional modules 1172 d. In some embodiments, the one ormore fourth respective functional modules may include a first and asecond power cell functional modules 1172 d-i-1172 d-ii. In someexamples, the one or more fourth respective functional modules 1172 dmay include a charging system including a solar panel 1176 extendingbetween the first power cell functional module 1172 d-i and the secondpower cell functional module 1172 d-ii. As shown in FIG. 11D, arespective functional module of the one or more fourth respectivefunctional modules may be attached to the chassis 1103 of the rover1102, such that the interior portions of the chassis 1103 at leastpartially surround the respective functional module of the one or morefourth respective functional modules. As discussed above with referenceto FIG. 11A, in some embodiments, the one or more fourth respectivefunctional modules may each be configured to attach to the chassis 1103of the rover 1102 via a plurality of attachment elements (not shown).For example, the plurality of attachment elements may correspond to aplurality of latch receptacles. In some embodiments, the plurality ofattachment elements may correspond to the plurality of latch receptaclesof the modular payload described herein (e.g., the same sizes,placements, relative spatial arrangements, and/or orientations as latchreceptacles 454 of the modular payloads 452 a-452 b in FIG. 4 ).Accordingly, the rover 1102 may be configured to individually retrieveeach of the one or more fourth respective functional modules accordingto any of the processes described previously with reference to FIGS.5A-5H.

As mentioned above, when the one or more fourth respective functionalmodules are individually attached to the chassis 1103 of the rover 1102,the ECU of the rover may operate the rover 1102 to perform one or moresolar farm deployment operations over a respective region of the (e.g.,lunar) surface. For example, the one or more solar farm deploymentoperations may include deploying the solar panel between a firstrespective location and a second respective location on the surface onwhich the plurality of propulsion components (e.g., 1115) of the rover1102 is placed. The first power cell functional module 1172 d-i may bepositioned (e.g., already placed) at the first respective location onthe surface. In some embodiments, the second power cell functionalmodule 1172 d-ii may be retrieved at or near the first respectivelocation on the surface. When the ECU determines that the second powercell functional module 1172 d-ii is attached to the chassis 1103 of therover 1102 (e.g., that the plurality of hooks of the rover latch systemhave engaged with the plurality of attachment elements of the secondpower cell functional module 1172 d-ii), the rover ECU may selectivelyoperate the plurality of propulsion components (e.g., 1115) to cause amotion of each of the propulsion components and a movement of the rover1102 and the second power cell functional module 1172 d-ii attached tothe chassis 1103 of the rover 1102 in a respective direction toward thesecond respective location at which the second power cell functionalmodule 1172 d-ii will be deposited. As shown in FIG. 11D, as the rover1102 travels toward the second respective location, a length of thesolar panel 1176 may increase (e.g., the solar panel 1176 may beextended) between the first power cell functional module 1172 d-i andthe second power cell functional module 1172 d-ii. For example, thesolar panel 1176 may be expandable (e.g., the solar panel 1176 comprisesan adjustable surface)—the solar panel 1176 may initially be foldedbetween the first power cell functional module 1172 d-i and the secondpower cell functional module 1172 d-ii—and movement of the roveroptionally causes the solar panel 1176 to become expanded (e.g.,unfolded and/or flattened due to a pulling of a second end of the solarpanel 1176 attached to the second power cell functional module 1172d-ii).

When the rover 1102 reaches the second respective location on thesurface, the rover ECU may operate the plurality of propulsioncomponents (e.g., 1115) and/or the plurality of control legs (e.g.,1113) of the rover 1102 to deposit the second power cell functionalmodule 1172 d-ii at the second respective location on the surface. Forexample, the rover ECU may cease driving the plurality of propulsioncomponents and may change respective orientations of the plurality ofcontrol legs to cause the chassis 1103 to be lowered toward the surfaceto deposit the second power cell functional module 1172 d-ii on thesurface. In some embodiments, the rover ECU may control the latch systemof the rover 1102 to cause the plurality of hooks of the latch system todisengage from the plurality of attachment elements of the second powercell functional module 1172 d-ii, and to deposit the second power cellfunctional module 1172 d-ii, and thus the solar panel 1176, onto the(e.g., lunar) surface. As mentioned above, in some embodiments, the oneor more fourth respective functional modules 1172 d may include acharging system (e.g., electrically) coupled to the solar panel 1176. Insome embodiments, the charging system may be or may include chargingcells (e.g., battery cells) configured to store power collected via thesolar panel 1176. The power stored in the charging cells of the firstpower cell functional module 1172 d-i and the second power cellfunctional module 1172 d-ii may then be used to power various systems onthe (e.g., lunar) surface, such as electrical equipment, rovers,electrically motorized machinery, lunar outposts, and the like.

In some embodiments, the chassis of the rover may be configured tointerface with a performance attachment for performing one or moresearch and rescue operations. For example, as shown in FIG. 11E, therover 1102 may be interfaced with a performance attachment 1172 e. Insome embodiments, the performance attachment 1172 e may include atransportation element (e.g., a gurney) on which an immobilized user maybe securely placed. As shown in FIG. 11E, the performance attachment1172 e may be attached to the chassis 1103 of the rover 1102, such thatthe interior portions 1101 of the chassis 1103 at least partiallysurround the performance attachment 1172 e. As shown in FIG. 11E, theperformance attachment 1172 e may be physically coupled (e.g., tied,fixed, snapped, etc.) to the interior portions of the chassis 1103. Forexample, the interior portions of the chassis 1103 may include fasteningpoints at which the performance attachment 1172 e may be coupled.Additionally or alternatively, in some embodiments, the performanceattachment 1172 e may be attached (e.g., coupled, tied, fixed, snapped,etc.) to the chassis 1103 via one or more of the plurality of hooks(e.g., corresponding to the plurality of hooks 553 in FIGS. 5F-5H)disposed within the sides of the chassis 1103.

As mentioned above, when the performance attachment 1172 e is attachedto the chassis 1103 of the rover 1102, the ECU of the rover may causethe rover 1102 to perform one or more search and rescue operations at arespective location on the (e.g., lunar) surface. For example, the oneor more search and rescue operations may include locating an immobilizeduser (e.g., immobilized astronaut) at the respective location, andtransporting the immobilized user to a safe location (e.g., forreceiving care, treatment, etc.) on the surface on which the pluralityof propulsion components 1115 of the rover 1102 is placed. When the ECUdetermines that the performance attachment 1172 e is attached to thechassis 1103 of the rover 1102, the rover ECU may selectively operatethe plurality of propulsion components 1115 to cause a motion of each ofthe propulsion components 1115 and a movement of the rover 1102 and theperformance attachment 1172 e attached to the chassis 1103 of the rover1102 in a respective direction toward the respective location at whichthe immobilized user is located.

When the rover 1102 reaches the respective location on the surface(e.g., using image data captured via the one or more sensors (e.g.,corresponding to the one or more sensors 1020 in FIG. 10 ) to locate theimmobilized user 1171), the rover ECU may operate the plurality ofpropulsion components 1115 and/or the plurality of control legs 1113 toretrieve the immobilized user 1171. For example, the rover ECU may ceasedriving the plurality of propulsion components 1115 and may changerespective orientations of the plurality of control legs to cause thechassis 1103 to be lowered toward the surface to place the performanceattachment 1172 e on the surface. The immobilized user 1171 may beplaced onto the performance attachment 1172 e (e.g., by one or moreother users), and the chassis 1103 may be raised to an uprightorientation, as shown in FIG. 11E. The rover ECU may then operate theplurality of propulsion components 1115 to produce a motion of the rover1102 for transporting the immobilized user 1171 to the safe location.

Thus, as outlined above, a variety of diverse payloads (e.g., thefunctional modules and performance attachments) may be interfaced withthe chassis 1103 of the rover 1102 to perform a variety of actionsinvolving the diverse payloads. Thus, one advantage of the disclosedrover and associated processes is the provision for adaptiveutility—namely, transporting modular payloads and operating diversepayloads while requiring little to no manual input from a user.

It should be understood that additional and/or alternative functionalmodules may be interfaced with the rover 1102 for performing one or morerespective actions involving the functional modules. For example, thechassis 1103 of the rover 1102 may be interfaced with reactor functionalmodules for transporting and/or deploying kilo power reactors across the(e.g., lunar) surface. As another examples, the chassis 1103 of therover 1102 may be interfaced with beacon functional modules fortransporting and/or deploying navigation/landing beacons across thesurface.

Universal Chassis Locking Interface and Associated Processes

Attention is now directed towards examples of a chassis lockinginterface that may be utilized to transport and/or deposit the rover.The chassis locking interface may correspond to a locking interface of amodular payload configured to be retrieved, transported, and/ordeposited by the rover. When the modular payload is interfaced with thechassis of the rover, the chassis locking interface may enable the roverand the modular payload attached to the rover to be transported and/ordeposited (e.g., together) by an external system, as described below.

FIG. 12 illustrates an example of a chassis locking interface of a rover1202 according to some embodiments of the disclosure. In someembodiments, the rover 1202 optionally corresponds to rover 702, 602,502, and/or 202 shown in FIGS. 7A-7E, FIGS. 6A-6B, FIGS. 5A-5H, and/orFIGS. 2A-2B, respectively. As discussed herein, the rover 1202 may beconfigured to retrieve, transport, and/or deposit a modular payload1252. In some embodiments, the modular payload 1252 optionallycorresponds to modular payload 452, 552, 652, and/or 752 shown in FIG. 4, FIGS. 5A-5G, FIGS. 6A-6B, and/or FIGS. 7C-7D. As discussed below, insome embodiments, the rover 1202 and the modular payload 1252 attachedto the chassis 1203 of the rover 1202 may be configured to betransported and/or deposited via the chassis locking interface of therover 1202. In some embodiments, the rover 1202 may be configured to betransported and/or deposited via the chassis locking interface of therover 1202.

As shown in FIG. 12 , the rover 1202 may be in a collapsed/loweredstate, such that respective orientations of the plurality of controllegs 1213 of the rover 1202 are elevated with respect to a reference(e.g., the surface on which the plurality of propulsion components 1215is placed) and the chassis 1203 of the rover 1202 is in a lowered statewith respect to a top surface of the modular payload 1252. For example,the plurality of control legs 1213 may be raised with respect to thesurface below the rover 1202 according to any of the processes describedpreviously with reference to FIGS. 5A-5E. As shown, in the collapsedstate, the plurality of control legs 1213 of the rover 1202 may (e.g.,at least partially) abut the first side 1205 and the second side 1209,such that the rover has a (e.g., substantially) cuboidal shape in thecollapsed state. In some scenarios, such as during initial offloadingfrom a carrier (e.g., a planetary (e.g., lunar) lander) onto the (e.g.,lunar) surface, the rover may be arranged and/or positioned among cargo(e.g., a plurality of equipment, modular payloads, other rovers, and thelike). As discussed in more detail below with reference to FIGS.13A-13C, the cuboidal shape of the rover 1202 in the collapsed stateenables the rover 1202 to be more efficiently and modularly loaded(e.g., stacked, stowed, etc.) on the carrier, which maximizes the numberand/or size of cargo that may be stowed on the carrier.

In some embodiments, the rover 1202 may be configured to attach to amodular payload 1252 while the rover 1202 is in the collapsed state. Asshown, the modular payload 1252 may be attached to the chassis 1203,such that interior portions of the chassis 1203 at least partiallysurround the modular payload 1252 and a bottom surface of the medialmember (e.g., medial member 207 in FIGS. 2A-2B) of the chassis 1203abuts (e.g., or is within a threshold distance (e.g., 0.5, 1, 1.5, 2, 3,4, 5, etc. cm) from) the top surface of the modular payload 1252. Asmentioned above, the plurality of control legs 1213 may be (e.g., fully)raised with respect to the surface beneath the rover 1202 when the rover1202 is in the collapsed state. As shown, while the plurality of controllegs 1213 are in the raised position, the chassis 1203 of the rover 1202may still accommodate (e.g., be configured to attach to and/or beattached to) the modular payload 1252. For example, a sufficientclearance (e.g., spacing or gap) is provided between each of theplurality of control legs 1213 and a respective portion (e.g., a side)of the modular payload 1252. Accordingly, as discussed in more detailwith reference to FIGS. 13A-13C, the rover 1202 and the modular payload1252 attached to the chassis 1203 of the rover 1202 may be configured tobe transported and/or deposited while the rover 1202 is in the collapsedstate of FIG. 12 .

As described herein, the modular payload 1252 may comprise a pluralityof latch receptacles (e.g., corresponding to the plurality of latchreceptacles 454 in FIG. 4 ) via which the rover 1202 may latch with themodular payload 1252. In some embodiments, the chassis 1203 of the rover1202 may comprise a locking interface including a plurality ofattachment elements. In some embodiments, the plurality of attachmentelements is optionally a second plurality of latch receptacles, whichmay correspond to (e.g., have the same sizes, placements, shapes and/orrelative spatial orientations as) the plurality of latch receptacles ofthe modular payload 1252. For example, as shown in the detailed view1231 in FIG. 12 , which depicts a cross-section of a central portion ofthe second side 1209 of the chassis 1203, the chassis 1203 of the rover1202 may include the second plurality of latch receptacles 1278. In someembodiments, the second plurality of latch receptacles may be disposed(e.g., externally) on the first side 1205 (e.g. corresponding to thefirst side 205 in FIGS. 2A-2B) and (e.g., externally) on the second side1209 (e.g., corresponding to the second side 209 in FIGS. 2A-2B) of thechassis 1203 of the rover 1202. As shown in FIG. 12 , in someembodiments, the second plurality of latch receptacles 1278 may bedisposed in an external upper portion (e.g., at least partiallyin/through a top surface) of the first side 1205 and an external upperportion of the second side 1209 of the chassis 1203. For example, asshown in the view 1231, the second plurality of latch receptacles 1278may be disposed in the upper 2, 5, 10, 15, 17, 20, etc. percent of thefirst side 1205 and the second side 1209 of the chassis 1203. In someembodiments, the second plurality of latch receptacles 1278 may bepositioned centrally in the upper portions of the first side 1205 andthe second side 1209 of the chassis 1203. For example, as shown in FIG.12 , the second plurality of latch receptacles 1278 may include at leasta first latch receptacle and a second latch receptacle on the secondside 1209 of the chassis 1203. The first latch receptacle and the secondlatch receptacle may be disposed on the upper portion of the second side1209 adjacent to the portion of the medial member (e.g., medial member207) attached to the upper portion of the second side 1209 (e.g., abovethe components of the latch system 1206 configured to latch with themodular payload 1252). In some embodiments, a respective spatialarrangement of the second plurality of latch receptacles 1278 of thechassis may correspond to (e.g., may be the same as, or substantiallythe same as (e.g., within 1, 3, 5, 10, 20 or 50 percent of being thesame size as)) a respective spatial arrangement of the plurality oflatch receptacles 1254 of the modular payload 1252. As used herein, theterm “spatial arrangement” refers to the particular location and/ororientation of respective components and the spacing between therespective components. For example, the first latch receptacle and thesecond latch receptacle of the second plurality of latch receptacles1278 may be disposed at a respective distance from each other (e.g., 5cm, 6 cm, 7 cm, 8.5 cm, 10 cm, 12 cm, 15 cm, etc.). In some embodiments,a first respective latch receptacle and a second respective latchreceptacle of the plurality of latch receptacles 1254 of the modularpayload 1252 may be disposed at the respective distance from each other.

Additionally or alternatively, in some embodiments, a respective spatialarrangement of the second plurality of latch receptacles 1278 may notcorrespond to a respective spatial arrangement of the plurality of latchreceptacles 1254 of the modular payload 1252. For example, the firstlatch receptacle and the second latch receptacle of the second pluralityof latch receptacles 1278 may be disposed at a first respective distancefrom each other (e.g., 5 cm, 6 cm, 7 cm, 8.5 cm, 10 cm, 12 cm, 15 cm,etc.). The first respective latch receptacle and the second respectivelatch receptacle of the plurality of latch receptacles of the modularpayload 1252 may be disposed at a second respective distance, differentfrom the first respective distance, from each other. In someembodiments, a first number of the second plurality of latch receptacles1278 disposed on the upper portion of the first side 1205 of the chassis1203 may share a respective spatial arrangement with a second number ofthe second plurality of latch receptacles 1278 disposed on the upperportion of the second side 1209 of the chassis 1203. For example, thesecond plurality of latch receptacles may further include a third latchreceptacle and a fourth latch receptacle. In some embodiments, the firstlatch receptacle and the second latch receptacle may be disposed in theupper portion of the first side 1205 of the chassis 1203, and the thirdlatch receptacle and the fourth latch receptacle of the second pluralityof latch receptacles 1278 may be disposed in the upper portion of thesecond side 1209 of the chassis 1203. The first latch receptacle and thesecond latch receptacle may be disposed on the first side 1205 at arespective distance from each other. Likewise, the third latchreceptacle and the fourth latch receptacle may be disposed on the secondside 1209 of the chassis at the respective distance from each other.Thus, as an example, the second plurality of latch receptacles 1278disposed on the first side 1205 and on the second side 1209 of thechassis 1203 may mirror each other.

Additionally, for example, the first latch receptacle and the thirdlatch receptacle of the second plurality of latch receptacles 1278 maybe disposed a respective distance apart from each other across thechassis (e.g., in a direction parallel to the medial member of thechassis) 1203 (e.g., a width of or less than the width of the interiorportions (e.g., 201 in FIG. 2A) of the chassis 1203, such as 0.5 m, 0.75m, 1 m, 1.5 m, 2 m, 3 m, 3.5 m, etc.). Likewise, the second latchreceptacle and the fourth latch receptacle of the second plurality oflatch receptacles 1278 may be disposed at the respective distance apartfrom each other across the chassis 1203. In some embodiments, a crossdistance of the plurality of latch receptacles 1254 of the modularpayload 1252 may share the spatial arrangement above. For example, thefirst respective latch receptacle and a third respective latchreceptacle of the plurality of latch receptacles 1254 of the modularpayload 1252 may be disposed the respective distance apart from eachother across the modular payload 1252 (e.g., a width of or less than thewidth of the modular payload 1252, which may be the same as that of theinterior portions of the chassis 1203). Likewise, the second respectivelatch receptacle and a fourth respective latch receptacle of theplurality of latch receptacles 1254 of the modular payload 1252 may bedisposed the respective distance apart from each other across themodular payload 1252.

In some embodiments, a shape of each of the second plurality of latchreceptacles 1278 of the chassis 1203 may correspond to (e.g., may be thesame as, or substantially the same as (e.g., within 1, 3, 5, 10, 20 or50 percent of being the same size as)) a shape of each of the pluralityof latch receptacles 1254 of the modular payload 1252. For example, asshown in the detailed view 1231 in FIG. 12 , a shape of the firstrespective latch receptacle of the plurality of latch receptacles 1254of the modular payload 1252 may be the same as or substantially the sameas a shape of the first latch receptacle of the second plurality oflatch receptacles 1278 of the chassis 1203. Additionally oralternatively, in some embodiments, a size of each of the secondplurality of latch receptacles 1278 of the chassis may correspond to(e.g., may be the same as, or substantially the same as (e.g., within 1,3, 5, 10, 20 or 50 percent of being the same size as)) a size of each ofthe plurality of latch receptacles 1254 of the modular payload 1252. Forexample, as shown in FIG. 12 , a depth, width, and/or height of thefirst respective latch receptacle of the plurality of latch receptacles1254 of the modular payload 1252 may be the same as, substantially thesame as, or similar to a depth, width, and/or height of the first latchreceptacle of the second plurality of latch receptacles 1278 of thechassis 1203.

As mentioned above, the rover 1202 may be configured to be transportedand/or deposited via the chassis locking interface (e.g., via the secondplurality of latch receptacles 1278). As shown in FIG. 12 , the rover1202 may be configured to attach to a lifting block 1277 of an externalsystem (e.g., a crane system) for lifting and/or transporting the rover1202. For example, the lifting block 1277 may comprise a plurality ofhooks/latches/appendages (not shown) configured to interlock with thesecond plurality of latch receptacles 1278 of the chassis 1203 and/orthe plurality of latch receptacles 1254 of the modular payload 1252. Insome embodiments, the lifting block 1277 may attach to the chassis 1203of the rover 1202 to transport and/or deposit both the rover 1202 andthe modular payload 1252. For example, as shown in FIG. 12 , while therover 1202 is in the collapsed state, the chassis 1203 of the rover 1202may be attached to the modular payload 1252 via the latch system 1206(e.g., via the engagement of the plurality of hooks 1253 with theplurality of latch receptacles 1254 of the modular payload 1252). Insome embodiments, the latch system 1206 optionally corresponds to thelatch system 506 shown in FIGS. 5F-5H. Additionally, in someembodiments, while the rover 1202 is in the collapsed state, theplurality of propulsion components 1215 may be raised to a sufficientelevation (e.g., with respect to the surface) such that the rover 1202and the modular payload 1252 combination rests on the surface via abottom surface of the modular payload 1252, rather than via theplurality of propulsion components 1215 (e.g., to avoid unintendedand/or undesired rolling, spinning, or movement of the rover 1202 and/orthe modular payload 1252 as the rover 1202 and modular payload 1252combination rests on the surface). The latches of the lifting block 1277may be attached to the chassis 1203 of the rover 1202 at the secondplurality of latch receptacles 1254 to transport and/or deposit therover 1202 and the modular payload 1252 attached to the rover 1202.Thus, the rover 1202 and the modular payload 1252 may effectively form asingle payload transportable and/or deployable using a suitable liftingmeans (e.g., such as lifting block 1277). Thus, one advantage ofconfiguring the rover with the chassis locking interface is the ease ofintegration of the rover into existing payload transportation anddeposition systems already configured for transporting and/or depositingmodular payloads having the locking interface.

FIGS. 13A-13C illustrate an example of depositing a rover 1302 and arespective modular payload 1352 a onto a surface 1359 using an externalsystem 1379 according to some embodiments of the disclosure. In someembodiments, the rover 1302 optionally corresponds to rover 1202, 702,602, 502, and/or 202 shown in FIG. 12 , FIGS. 7A-7E, FIGS. 6A-6B, FIGS.5A-5H, and/or FIGS. 2A-2B, respectively. In some embodiments, themodular payloads 1352 and 1352 a optionally correspond to modularpayload 1252, 552, and/or 452 shown in FIG. 12 , FIGS. 5A-5H, and/orFIG. 4 . As described above with reference to FIG. 12 , the rover 1302may be provided with a chassis locking interface including a pluralityof attachment elements (e.g., the second plurality of latch receptacles1254) configured to be attached to an external system for transportingand/or depositing the rover 1302. As discussed below, in someembodiments, the external system may belong to a carrier configured todeposit the rover 1302 and a plurality of modular payloads 1352 onto thesurface 1359.

As an example, as shown in FIG. 13A, the external system may be a cranesystem 1379 that is attached to a planetary lander (e.g., lunar lander)1382 on the (e.g., lunar) surface 1359. As shown, the crane system 1379may include the lifting block 1377 (e.g., corresponding to lifting block1277 in FIG. 12 ) configured to engage with the chassis 1303 of therover 1302. As shown in FIG. 13A, the rover 1302 may be placed on asurface or within an area of the planetary lander 1382 among a pluralityof modular payloads 1352. As discussed previously above with referenceto FIG. 12 , the rover 1302 may be situated on the surface of theplanetary lander 1382 in the collapsed state, such that the rover 1302has a substantially cuboidal shape, allowing the rover 1302 to bemodularly loaded amongst the plurality of modular payloads 1352, asshown in FIG. 13A. In the example of FIGS. 13A-13C, the crane system1379 of the planetary lander 1382 may be operated (e.g., autonomously,externally controlled, manually controlled, etc.) to lift the rover 1302from amongst the modular payloads 1352 and deposit the rover 1302 ontothe surface 1359.

As shown in FIG. 13A, the lifting block 1377 may be lowered (e.g., withrespect to the surface 1359, or the top surface of the planetary landeron which the rover 1302 is placed) toward the top surface of the chassis1303 of the rover 1302 and may attach to the chassis locking interfaceof the rover 1302. For example, the hooks/appendages of the liftingblock 1377 may be engaged with the plurality of latch receptacles (e.g.,1278) of the chassis 1303 of the rover 1302. As shown in FIG. 13B, thelifting block 1377 may be raised (e.g., with respect to the surface1359, or the top surface of the planetary lander on which the rover 1302was placed) to lift the rover 1302 from amongst the plurality of modularpayloads 1352. As shown, the rover 1302 may be raised/lifted with thelifting block 1377. For example, the lifting block 1377 may lift therover 1302 with respect to the top surface of the planetary lander 1382on which the rover 1302 was placed. The lifting block 1377 may thendeposit the rover 1302 onto the surface 1359. As discussed above withreference to FIG. 12 , in some embodiments, the rover 1302, while in thecollapsed state, may be attached to a modular payload. As shown in FIG.13B, the chassis 1303 of the rover 1302 may be attached to a respectivemodular payload 1352 a. As such, when the lifting block 1377 lifts therover 1302, the respective modular payload 1352 a is also lifted withrespect to the top surface of the planetary lander 1382 on which therespective modular payload 1352 a was placed. Thus, the rover 1302 andthe respective modular payload 1352 a may be deposited on the surface1359 via the lifting block 1377.

As shown in FIG. 13C, the lifting block 1377 may be lowered by the cranesystem 1379 toward the surface 1359 to deposit the rover 1302 and themodular payload 1352 a onto the surface 1359. For example, the liftingblock 1377 may be lowered toward the surface 1359 until a bottom surfaceof the respective modular payload 1352 a contacts (e.g., or is loweredwithin a threshold distance (e.g., 0.5 cm, 1 cm, 1.5 cm, 2 cm, 2.5 cm, 3cm, etc.) of) the surface 1359. In an instance in which the rover is notpowered on (e.g., the rover is in an off state or in a low-power stateand/or a sleep state), the power system (e.g., corresponding to powersystem 108 in FIG. 1A) may be operated (e.g., by the rover ECU and/orvia external or manual control) to supply power to the various systemsof the rover 1302. For example, the latch system (e.g., corresponding tolatch system 506 in FIGS. 5F-5H) of the rover 1302 may be operated(e.g., by the rover ECU) to disengage from the respective modularpayload 1352 a, thus depositing the respective modular payload 1352 aonto the surface 1359, as shown in FIG. 13C. The rover 1302 may then beoperated (e.g., by the rover ECU) to raise the chassis 1303 of the roverwith respect to the surface 1359, as shown in FIG. 13C, and may thenproceed to retrieving a second modular payload or performing anotheraction as instructed by the rover ECU.

It should be understood that the planetary lander 1382 and the cranesystem 1379 (e.g., including the lifting block 1377) shown in FIGS.13A-13C are merely examples and that additional and/or alternativecarriers and systems may be utilized to transport and/or deposit therover 1302 and/or the modular payloads 1352.

Therefore, according to the above, some embodiments of the disclosureare directed to a vehicle, comprising: a chassis, comprising a firstplurality of attachment elements configured to be attached to anexternal system for retrieving and transporting the vehicle with respectto a reference by the external system, wherein the attachment elementsincluded in the first plurality of attachment elements are arranged witha respective spatial arrangement relative to each other, and a payloadretrieval system configured to attach the chassis to a respectivepayload at a second plurality of attachment elements included in therespective payload, wherein the attachment elements included in thesecond plurality of attachment elements are arranged with the respectivespatial arrangement relative to each other; a plurality of control legscoupled to the chassis; a plurality of propulsion components coupled tothe plurality of control legs; and one or more processors incommunication with the payload retrieval system, the one or moreprocessors programmed to selectively control the payload retrievalsystem to attach the chassis to the respective payload at the secondplurality of attachment elements.

Additionally or alternatively, in some embodiments, the referenceincludes a surface on which the plurality of propulsion components ofthe vehicle is placed.

Additionally, or alternatively, in some embodiments, the external systemincludes a crane system.

Additionally or alternatively, in some embodiments, the external systemincludes a planetary lander.

Additionally or alternatively, in some embodiments, the first pluralityof attachment elements includes a first plurality of latch receptacles,the second plurality of attachment elements includes a second pluralityof latch receptacles, and when the respective payload is attached to thechassis at the second plurality of latch receptacles, the vehicle andthe respective payload are configured to be retrieved and transportedtogether via the external system attached to the first plurality oflatch receptacles.

Additionally or alternatively, in some embodiments, the first pluralityof latch receptables have a same size and a same shape as the secondplurality of latch receptacles.

Additionally or alternatively, in some embodiments, the chassis furthercomprises a first side and an opposite second side, and a medial memberextending between an upper portion of the first side and an upperportion of the second side, wherein the medial member at least partiallyforms a top of the chassis. In some embodiments, the payload retrievalsystem comprises a plurality of hooks configured to selectively protrudefrom interior portions of the chassis to attach to the second pluralityof attachment elements.

Additionally or alternatively, in some embodiments, the one or moreprocessors are programmed to control the payload retrieval system toselectively cause the plurality of hooks to protrude from the interiorportions of the chassis to engage with at least a portion of the secondplurality of attachment elements.

Additionally or alternatively, in some embodiments, the first pluralityof latch receptacles is disposed in first regions of upper portions ofthe first side and the second side of the chassis, the second pluralityof latch receptacles is disposed in first respective regions of upperportions of a first side and a second side of the respective payload,and the first regions correspond to the first respective regions.

Additionally or alternatively, in some embodiments, the first pluralityof latch receptacles includes a first latch receptacle, a second latchreceptacle, a third latch receptacle and a fourth latch receptacle, thefirst latch receptacle and the second latch receptacle are disposed inthe first region of the upper portion of the first side of the chassis,and the third latch receptacle and the fourth latch receptacle aredisposed in the first region of the upper portion of the second side ofthe chassis.

Additionally or alternatively, in some embodiments, the second pluralityof latch receptacles includes a first respective latch receptacle, asecond respective latch receptacle, a third respective latch receptacleand a fourth respective latch receptacle, the first respective latchreceptacle and the second respective latch receptacle are disposed inthe first respective region of the upper portion of the first side ofthe respective payload, and the third respective latch receptacle andthe fourth respective latch receptacle are disposed in the firstrespective region of the upper portion of the second side of therespective payload.

Additionally or alternatively, in some embodiments, the first latchreceptacle and the second latch receptacle are disposed a first distanceapart in the first region of the upper portion of the first side of thechassis, the third latch receptacle and the fourth latch receptacle aredisposed the first distance apart in the first region of the upperportion of the second side of the chassis, and an axis through the firstlatch receptacle and the third latch receptacle is parallel to an axisthrough the second latch receptacle and the fourth latch receptacle.

Additionally or alternatively, in some embodiments, the first latchreceptacle and the third latch receptacle are disposed a first distanceapart from the first region of the upper portion of the first side tothe first region of the upper portion of the second side of the chassis,respectively, and the first respective latch receptacle and the thirdrespective latch receptacle are disposed the first distance apart fromthe first respective region of the upper portion of the first side tothe first respective region of the upper portion of the second side ofthe respective payload, respectively.

Additionally or alternatively, in some embodiments, the first respectivelatch receptacle and the second respective latch receptacle are disposeda second distance apart in the first respective region of the upperportion of the first side of the respective payload, the thirdrespective latch receptacle and the fourth respective latch receptacleare disposed the second distance apart in the first region of the upperportion of the second side of the respective payload, and an axisthrough the first respective latch receptacle and the third respectivelatch receptacle is parallel to an axis through the second respectivelatch receptacle and the fourth respective latch receptacle.

Additionally or alternatively, in some embodiments, the first distanceis equal to the second distance.

Additionally or alternatively, in some embodiments, the payloadretrieval system is further configured to attach the chassis to arespective functional module, the respective functional modulecomprising a third plurality of attachment elements, the plurality ofcontrol legs includes a first control leg and a second control leg, theplurality of propulsion components includes a first propulsion componentand a second propulsion component, the first propulsion componentcoupled to the first control leg, and the second propulsion componentcoupled to the second control leg, and the one or more processors are incommunication with the first control leg and the second control leg andthe first propulsion component and the second propulsion component. Insome embodiments, the one or more processors are programmed toselectively control the first control leg and the second control leg andselectively control the first propulsion component and the secondpropulsion component to perform a respective action involving therespective functional module.

Additionally or alternatively, in some embodiments, the respectiveaction includes retrieval of the respective functional module. In someembodiments, the one or more processors are programmed to: selectivelycontrol the first control leg and the second control leg to lower thechassis with respect to the reference; and selectively control thepayload retrieval system to attach the chassis to the respectivefunctional module at the third plurality of attachment elements.

Additionally or alternatively, in some embodiments, the respectiveaction includes movement of the respective functional module in arespective direction. In some embodiments, the one or more processorsare programmed to, in accordance with a determination that the chassisis attached to the respective functional module, selectively control thefirst propulsion component and the second propulsion component to causea movement of the vehicle, and thus the respective functional module, inthe respective direction.

Additionally or alternatively, in some embodiments, the respectivefunctional module includes a respective system having a drill, therespective action includes drilling into a surface on which the firstpropulsion component and the second propulsion component are placed, andthe one or more processors are in communication with the respectivesystem of the respective functional module, the one or more processorsprogrammed to, in accordance with the determination that the chassis isattached to the respective functional module, selectively control therespective system to operate the drill to cause a drilling into thesurface on which the vehicle is placed.

Additionally or alternatively, in some embodiments, the respectivefunctional module includes a respective system having a gurney, and therespective action includes transportation of an immobilized user. Insome embodiments, the one or more processors are programmed to, inaccordance with the determination that the chassis is attached to therespective functional module: selectively control the first control legand the second control leg to lower the chassis with respect to thereference for retrieving the immobilized user using the gurney; andselectively control the first propulsion component and the secondpropulsion component to cause the movement of the vehicle to transportthe immobilized user.

Additionally or alternatively, in some embodiments, the respectivefunctional module includes a respective system having a blade, and therespective action includes excavation of a surface on which the firstpropulsion component and the second propulsion component are placed. Insome embodiments, the one or more processors are in communication withthe respective system, the one or more processors programmed to, inaccordance with the determination that the chassis is attached to therespective functional module: selectively control the respective systemand/or selectively control the plurality of control legs to lower theblade to a first elevation with respect to the surface; and selectivelycontrol the first propulsion component and the second propulsioncomponent to cause the movement of the vehicle to excavate the surfaceusing the blade.

Additionally or alternatively, in some embodiments, the respectivefunctional module includes a respective system having a solar panelassembly, and the respective action includes deployment of the solarpanel assembly on a surface on which the first propulsion component andthe second propulsion component are placed. In some embodiments, the oneor more processors are programmed to, in accordance with thedetermination that the chassis is attached to the respective functionalmodule: selectively control the first propulsion component and thesecond propulsion component to cause a movement of the vehicle in asecond respective direction; selectively control the first control legand the second control leg to lower the chassis with respect to thesurface; and selectively control the payload retrieval system to detachthe chassis from the respective functional module at the third pluralityof attachment elements and deposit the solar panel assembly on thesurface.

Some embodiments of the disclosure are directed to a non-transitorycomputer-readable storage medium storing instructions, which whenexecuted by one or more processors of a vehicle, cause the vehicle toperform a method. In some embodiments, the method comprises selectivelycontrolling a payload retrieval system of the vehicle to attach achassis of the vehicle to a respective payload at a plurality ofattachment elements, wherein the plurality of attachment elements isincluded in the respective payload, and the attachment elements includedin the plurality of attachment elements are arranged with a respectivespatial arrangement relative to each other.

Some embodiments of the disclosure are directed to a vehicle,comprising: a chassis comprising a first plurality of attachmentelements configured to be attached to an external system for retrievingand transporting the vehicle with respect to a reference by the externalsystem, wherein the attachment elements included in the first pluralityof attachment elements are arranged with a respective spatialarrangement relative to each other, and a payload retrieval systemconfigured to attach the chassis to a respective payload at a secondplurality of attachment elements included in the respective payload,wherein the attachment elements included in the second plurality ofattachment elements are arranged with the respective spatial arrangementrelative to each other; a plurality of control legs coupled to thechassis; and a plurality of propulsion components coupled to theplurality of control legs.

Additionally or alternatively, in some embodiments, the first pluralityof attachment elements includes a first plurality of latch receptacles,the second plurality of attachment elements includes a second pluralityof latch receptacles, and when the respective payload is attached to thechassis at the second plurality of latch receptacles, the vehicle andthe respective payload are configured to be retrieved and transportedtogether via the external system attached to the first plurality oflatch receptacles.

Additionally or alternatively, in some embodiments, the first pluralityof latch receptables have a same size and a same shape as the secondplurality of latch receptacles.

Additionally or alternatively, in some embodiments, the first pluralityof latch receptacles is disposed in first regions of upper portions ofthe first side and the second side of the chassis, the second pluralityof latch receptacles is disposed in first respective regions of upperportions of a first side and a second side of the respective payload,and the first regions correspond to the first respective regions.

Although examples have been fully described with reference to theaccompanying drawings, it is to be noted that various changes andmodifications will become apparent to those skilled in the art. Suchchanges and modifications are to be understood as being included withinthe scope of examples of this disclosure as defined by the appendedclaims.

What is claimed is:
 1. A vehicle comprising: a chassis, comprising: afirst plurality of attachment elements configured to be attached to anexternal system for retrieving and transporting the vehicle with respectto a reference by the external system, wherein the attachment elementsincluded in the first plurality of attachment elements are arranged witha respective spatial arrangement relative to each other; and a payloadretrieval system configured to attach the chassis to a respectivepayload at a second plurality of attachment elements included in therespective payload, wherein the attachment elements included in thesecond plurality of attachment elements are arranged with the respectivespatial arrangement relative to each other; a plurality of control legscoupled to the chassis; a plurality of propulsion components coupled tothe plurality of control legs; and one or more processors incommunication with the payload retrieval system, the one or moreprocessors programmed to selectively control the payload retrievalsystem to attach the chassis to the respective payload at the secondplurality of attachment elements.
 2. The vehicle of claim 1, wherein thereference includes a surface on which the plurality of propulsioncomponents of the vehicle is placed.
 3. The vehicle of claim 1, whereinthe external system includes a crane system.
 4. The vehicle of claim 3,wherein the external system includes a planetary lander.
 5. The vehicleof claim 1, wherein: the first plurality of attachment elements includesa first plurality of latch receptacles; the second plurality ofattachment elements includes a second plurality of latch receptacles;and when the respective payload is attached to the chassis at the secondplurality of latch receptacles, the vehicle and the respective payloadare configured to be retrieved and transported together via the externalsystem attached to the first plurality of latch receptacles.
 6. Thevehicle of claim 5, wherein the first plurality of latch receptableshave a same size and a same shape as the second plurality of latchreceptacles.
 7. The vehicle of claim 5, wherein: the chassis furthercomprises: a first side and an opposite second side; and a medial memberextending between an upper portion of the first side and an upperportion of the second side, wherein the medial member at least partiallyforms a top of the chassis; and the payload retrieval system comprises aplurality of hooks configured to selectively protrude from interiorportions of the chassis to attach to the second plurality of attachmentelements.
 8. The vehicle of claim 7, wherein the one or more processorsare programmed to control the payload retrieval system to selectivelycause the plurality of hooks to protrude from the interior portions ofthe chassis to engage with at least a portion of the second plurality ofattachment elements.
 9. The vehicle of claim 7, wherein: the firstplurality of latch receptacles is disposed in first regions of upperportions of the first side and the second side of the chassis; thesecond plurality of latch receptacles is disposed in first respectiveregions of upper portions of a first side and a second side of therespective payload; and the first regions correspond to the firstrespective regions.
 10. The vehicle of claim 9, wherein: the firstplurality of latch receptacles includes a first latch receptacle, asecond latch receptacle, a third latch receptacle and a fourth latchreceptacle; the first latch receptacle and the second latch receptacleare disposed in the first region of the upper portion of the first sideof the chassis; and the third latch receptacle and the fourth latchreceptacle are disposed in the first region of the upper portion of thesecond side of the chassis.
 11. The vehicle of claim 10, wherein: thesecond plurality of latch receptacles includes a first respective latchreceptacle, a second respective latch receptacle, a third respectivelatch receptacle and a fourth respective latch receptacle; the firstrespective latch receptacle and the second respective latch receptacleare disposed in the first respective region of the upper portion of thefirst side of the respective payload; and the third respective latchreceptacle and the fourth respective latch receptacle are disposed inthe first respective region of the upper portion of the second side ofthe respective payload.
 12. The vehicle of claim 11, wherein: the firstlatch receptacle and the second latch receptacle are disposed a firstdistance apart in the first region of the upper portion of the firstside of the chassis; the third latch receptacle and the fourth latchreceptacle are disposed the first distance apart in the first region ofthe upper portion of the second side of the chassis; and an axis throughthe first latch receptacle and the third latch receptacle is parallel toan axis through the second latch receptacle and the fourth latchreceptacle.
 13. The vehicle of claim 11, wherein: the first latchreceptacle and the third latch receptacle are disposed a first distanceapart from the first region of the upper portion of the first side tothe first region of the upper portion of the second side of the chassis,respectively; and the first respective latch receptacle and the thirdrespective latch receptacle are disposed the first distance apart fromthe first respective region of the upper portion of the first side tothe first respective region of the upper portion of the second side ofthe respective payload, respectively.
 14. The vehicle of claim 13,wherein: the first respective latch receptacle and the second respectivelatch receptacle are disposed a second distance apart in the firstrespective region of the upper portion of the first side of therespective payload; the third respective latch receptacle and the fourthrespective latch receptacle are disposed the second distance apart inthe first region of the upper portion of the second side of therespective payload; and an axis through the first respective latchreceptacle and the third respective latch receptacle is parallel to anaxis through the second respective latch receptacle and the fourthrespective latch receptacle.
 15. The vehicle of claim 14, wherein thefirst distance is equal to the second distance.
 16. The vehicle of claim1, wherein: the payload retrieval system is further configured to attachthe chassis to a respective functional module, the respective functionalmodule comprising a third plurality of attachment elements; theplurality of control legs includes a first control leg and a secondcontrol leg; the plurality of propulsion components includes a firstpropulsion component and a second propulsion component, the firstpropulsion component coupled to the first control leg, and the secondpropulsion component coupled to the second control leg; and the one ormore processors are in communication with the first control leg and thesecond control leg and the first propulsion component and the secondpropulsion component, the one or more processors programmed toselectively control the first control leg and the second control leg andselectively control the first propulsion component and the secondpropulsion component to perform a respective action involving therespective functional module.
 17. The vehicle of claim 16, wherein: therespective action includes retrieval of the respective functionalmodule; the one or more processors are programmed to: selectivelycontrol the first control leg and the second control leg to lower thechassis with respect to the reference; and selectively control thepayload retrieval system to attach the chassis to the respectivefunctional module at the third plurality of attachment elements.
 18. Thevehicle of claim 16, wherein: the respective action includes movement ofthe respective functional module in a respective direction; and the oneor more processors are programmed to: in accordance with a determinationthat the chassis is attached to the respective functional module:selectively control the first propulsion component and the secondpropulsion component to cause a movement of the vehicle, and thus therespective functional module, in the respective direction.
 19. Thevehicle of claim 18, wherein: the respective functional module includesa respective system having a drill; the respective action includesdrilling into a surface on which the first propulsion component and thesecond propulsion component are placed; and the one or more processorsare in communication with the respective system of the respectivefunctional module, the one or more processors programmed to, inaccordance with the determination that the chassis is attached to therespective functional module, selectively control the respective systemto operate the drill to cause a drilling into the surface on which thevehicle is placed.
 20. The vehicle of claim 18, wherein: the respectivefunctional module includes a respective system having a gurney; therespective action includes transportation of an immobilized user; andthe one or more processors are programmed to: in accordance with thedetermination that the chassis is attached to the respective functionalmodule: selectively control the first control leg and the second controlleg to lower the chassis with respect to the reference for retrievingthe immobilized user using the gurney; and selectively control the firstpropulsion component and the second propulsion component to cause themovement of the vehicle to transport the immobilized user.
 21. Thevehicle of claim 18, wherein: the respective functional module includesa respective system having a blade; the respective action includesexcavation of a surface on which the first propulsion component and thesecond propulsion component are placed; and the one or more processorsare in communication with the respective system, the one or moreprocessors programmed to: in accordance with the determination that thechassis is attached to the respective functional module: selectivelycontrol the respective system and/or selectively control the pluralityof control legs to lower the blade to a first elevation with respect tothe surface; and selectively control the first propulsion component andthe second propulsion component to cause the movement of the vehicle toexcavate the surface using the blade.
 22. The vehicle of claim 18,wherein: the respective functional module includes a respective systemhaving a solar panel assembly; the respective action includes deploymentof the solar panel assembly on a surface on which the first propulsioncomponent and the second propulsion component are placed; and the one ormore processors are programmed to: in accordance with the determinationthat the chassis is attached to the respective functional module:selectively control the first propulsion component and the secondpropulsion component to cause a movement of the vehicle in a secondrespective direction; selectively control the first control leg and thesecond control leg to lower the chassis with respect to the surface; andselectively control the payload retrieval system to detach the chassisfrom the respective functional module at the third plurality ofattachment elements and deposit the solar panel assembly on the surface.23. A non-transitory computer-readable storage medium storinginstructions, which when executed by one or more processors of avehicle, cause the vehicle to perform a method comprising: selectivelycontrolling a payload retrieval system of the vehicle to attach achassis of the vehicle to a respective payload at a plurality ofattachment elements; wherein the plurality of attachment elements isincluded in the respective payload, and the attachment elements includedin the plurality of attachment elements are arranged with a respectivespatial arrangement relative to each other.
 24. A vehicle comprising: achassis, comprising: a first plurality of attachment elements configuredto be attached to an external system for retrieving and transporting thevehicle with respect to a reference by the external system, wherein theattachment elements included in the first plurality of attachmentelements are arranged with a respective spatial arrangement relative toeach other; and a payload retrieval system configured to attach thechassis to a respective payload at a second plurality of attachmentelements included in the respective payload, wherein the attachmentelements included in the second plurality of attachment elements arearranged with the respective spatial arrangement relative to each other;a plurality of control legs coupled to the chassis; and a plurality ofpropulsion components coupled to the plurality of control legs.
 25. Thevehicle of claim 24, wherein: the first plurality of attachment elementsincludes a first plurality of latch receptacles; the second plurality ofattachment elements includes a second plurality of latch receptacles;and when the respective payload is attached to the chassis at the secondplurality of latch receptacles, the vehicle and the respective payloadare configured to be retrieved and transported together via the externalsystem attached to the first plurality of latch receptacles.
 26. Thevehicle of claim 25, wherein the first plurality of latch receptableshave a same size and a same shape as the second plurality of latchreceptacles.
 27. The vehicle of claim 25, wherein: the first pluralityof latch receptacles is disposed in first regions of upper portions of afirst side and a second side of the chassis; the second plurality oflatch receptacles is disposed in first respective regions of upperportions of a first side and a second side of the respective payload;and the first regions correspond to the first respective regions.